Solar Turbines Incorporated Patent applications |
Patent application number | Title | Published |
20160116168 | ROBUST INSULATED FUEL INJECTOR FOR A GAS TURBINE ENGINE - A fuel injector for a combustor of a gas turbine engine is disclosed. The fuel injector includes a flange, a fitting boss, a stem, a gas fuel passage, a gas fuel fitting, and a gas heat shield. The fitting boss protrudes from the flange. The stem extends from the flange. The gas fuel passage extends through the stem. The gas fuel fitting is joined to the fitting boss. The gas heat shield extends from the gas fuel fitting at least partially through the gas fuel passage. The gas heat shield is sized to form a gas heat shield gap between the gas heat shield and the stem at the gas fuel passage. | 04-28-2016 |
20160115874 | LINER GROMMET ASSEMBLY - A base for a grommet assembly of a combustion chamber is disclosed. The base includes a base body and a cooling extension. The base body includes a first body portion having a first hollow cylinder sector shape and a second body portion having a second hollow cylinder sector shape. The first portion is thicker than the second portion. The cooling extension includes a cylindrical portion with a third hollow cylinder sector shape and an annular portion. The cylindrical portion extends axially from the base body. The annular portion extends radially from the cylindrical portion distal to the base body. | 04-28-2016 |
20160110387 | PRODUCT LIFECYCLE MANAGEMENT SYSTEM - A method for providing documents and information of a product lifecycle management system to a user system is disclosed. The method includes locating a latest released drawing associated with the component part number in the product lifecycle management database. The method also includes aggregating a part displacement record for each version of the component into a part replacement report. The method further includes providing a graphical user interface to the user system that displays a download link to the latest released drawing and displays a link to the part replacement report with the download link and the link located within a single window. | 04-21-2016 |
20160102862 | METHOD FOR MANUFACTURING A MACHINE COMPONENT - A method for manufacturing a machine component includes obtaining a casted component, a forged component, or a component manufactured using additive fabrication such that the machine component has a wall exhibiting at least some porosity therethrough. The method further includes adding a filler material to on the wall to a pre-determined thickness, the filler material being configured to cover the porosity present in the wall. The method further includes finishing the component by performing a finishing operation. | 04-14-2016 |
20160084112 | DIAPHRAGM ASSEMBLY BOLTED JOINT STRESS REDUCTION - A spacer for a diaphragm assembly coupling is disclosed. The spacer includes a base, a spacing portion, and a spacing body edge. The base includes a base body including a base edge. The spacing portion includes a spacing body and a spacing flange. The spacing body extends from the base and includes an outer diameter that is smaller than that of the base. The spacing flange extends outward from the spacing body and is spaced apart from the base. The spacing body edge is located at an intersection of the spacing body and the base body. A reference line extending from the spacing body edge to the base edge forms an angle from 10 to 30 degrees with the spacer axis. | 03-24-2016 |
20160084095 | DIAPHRAGM ASSEMBLY WITH A PRESWIRLER - A preswirler for a gas turbine engine diaphragm assembly is disclosed herein. In embodiments, the preswirler includes an outer ring and an inner ring. The outer ring includes an outer ring face, a first contact protrusion, and a second contact protrusion. The first and second contact protrusions are spaced apart and extend from an outer body portion at the outer ring face. The inner ring is located inward from the outer ring. The inner ring includes an inner ring face and a third contact protrusion. The third contact protrusion extends in from an inner body portion and at the inner ring face. | 03-24-2016 |
20160033137 | LASER CLAD FUEL INJECTOR PREMIX BARREL - A fuel injector for a gas turbine engine may include a center body disposed about a longitudinal axis, and a premix barrel positioned radially outwardly from the center body to define an annular passageway between the center body and the premix barrel. The annular passageway may extend from an upstream end that is configured to be fluidly coupled to a compressor to a downstream end that is configured to be fluidly coupled to a combustor. The premix barrel may include a first portion at the upstream end and a second portion at the downstream end. The first portion may include a stainless steel material, and the second portion may include a nickel based superalloy material. The second portion may be coupled to the first portion by a laser clad coupling. | 02-04-2016 |
20160023869 | ASSEMBLY FOR MOVING A COMPONENT RELATIVE TO A CEILING OF AN ENGINE ENCLOSURE - An assembly for moving a component relative to a ceiling of an engine enclosure includes a first-class lever, and a harnessing mechanism. The first-class lever is formed in at least one of the ceiling and a structure disposed above the ceiling. The first-class lever has a first side, and a second side located proximal to an opening defined in the ceiling. The harnessing mechanism includes a flexible link having a first end and a second end. The first end is disposed on the first side and is configured to allow an effort to be applied thereto. The second end is disposed on the second side and is configured to releasably connect with the component. The second end may hoist or lower the component relative to the ceiling in response to the effort and based on a type of effort applied at the first end. | 01-28-2016 |
20150363545 | SYSTEM FOR AUTOMATED DESIGN OF MULTI-BODY MACHINE - A system for automated design of a machine having multiple driven bodies is disclosed. The system may have a multi-body database with at least one of a parts section and a launch code section. The system may also have one or more processors configured to cause a listing of components selectable for inclusion within a machine to be shown on a display device, and to receive a selection of an input component and the multiple driven bodies from the listing via an input device. The processors may also be configured to retrieve data regarding the selected input component and the multiple driven bodies from the at least one of the parts section and the launch code section, and to generate a design for at least one new support component in the machine based on the input component, the multiple driven bodies, and the data. | 12-17-2015 |
20150337737 | STARTER/GENERATOR COMBINATION WITH ALL VARIABLE FREQUENCY DRIVES - A gas turbine engine includes a compressor, a combustor adjacent the compressor, a turbine adjacent the combustor, a shaft, a motor, a primary variable frequency drive, an auxiliary variable frequency drive, and an auxiliary motor. The motor is coupled to the shaft. The primary variable frequency drive is electrically connected to the motor and an AC power source. The auxiliary variable frequency drive is electrically connected to the primary frequency drive. The auxiliary motor is electrically connected to the auxiliary variable frequency drive. | 11-26-2015 |
20150337678 | THERMOCOUPLE WITH A VORTEX REDUCING PROBE - A sensor assembly for a gas turbine engine is disclosed. The sensor assembly includes a bushing and a probe. The probe includes a body, an anti-vortex tip, and a tip end. The body extends from the bushing and includes a body surface. The body surface is a right circular cylinder with a first diameter. The anti-vortex tip extends from the body and includes an anti-vortex tip surface. The anti-vortex tip surface is a conical surface extending from the body surface to a second diameter at a taper angle from fourteen degrees to sixteen degrees. The tip end extends with a spherical shape from the anti-vortex tip. | 11-26-2015 |
20150328721 | RADIOGRAPHIC MARKERS FOR PARTIAL PENETRATION WELDED JOINTS - A weldment member for a gas turbine engine including a forward welding member and an aft welding member. The forward welding member has an annular shape with a forward welding face formed at one end. The forward welding face has a forward radiographic marking hole formed therein. The aft welding member has an annular shape with an aft welding face formed at one end. The aft welding face has an aft radiographic marking hole formed therein. The forward welding face is aligned with the aft welding face and the forward radiographic marking hole is angularly offset from the aft radiographic marking hole. | 11-19-2015 |
20150323188 | ENCLOSED GAS FUEL DELIVERY SYSTEM - A gas fuel delivery system is disclosed. A gas fuel delivery system includes a gas fuel system and a gas ring. The gas fuel delivery system includes an enclosure surrounding the gas fuel system. The enclosure includes a ventilation system. The enclosure includes fuel pipes connecting the gas fuel system to a fuel source and to a gas ring. Each fuel pipe includes an outer conduit and an inner conduit, wherein the inner conduit is enclosed by the outer conduit. The inner conduit is in fluid communication with the gas fuel system. | 11-12-2015 |
20150315973 | SYSTEM FOR DETECTING A FLASHBACK AND MITIGATING DAMAGE FROM THE FLASHBACK TO A COMBUSTION SYSTEM - A system is provided for detecting and mitigating damage from flashback in a combustion system. The combustion system includes an injector and a combustor. The system includes a supply line coupled to the combustor. The supply line defines an end configured to face with the combustor. The end is provided with a fusible component that is configured to melt in the event of a flashback and release an extinguishing agent into the combustor. | 11-05-2015 |
20150308337 | GAS TURBINE ENGINE COMPONENT WITH EMBEDDED DATA - A component for a gas turbine engine is disclosed. The component includes at least a first portion and a second portion, and a data representing matrix. The second portion includes a second portion surface. The data representing matrix is formed directly on the second portion surface and includes a plurality of contrasting cells arranged in a geometric pattern representing information about the component including test data, a serial number, and a part number. The plurality of contrasting cells includes a plurality of first cells and a plurality of second cells that contrast from the plurality of first cells. | 10-29-2015 |
20150300406 | COMPACT SQUEEZE FILM DAMPER BEARING - A bearing assembly for a rotary machine is disclosed herein. The bearing assembly includes a bearing housing, a squeeze film cylinder, a damper spring, and a journal bearing. The squeeze film cylinder is located within the bearing housing. The damper spring includes a first portion, a second portion, and a spring portion. The first portion is located proximal the first end. The second portion is located proximal the second end. The spring portion extends axially between the first portion and the second portion and is located within the bearing housing. | 10-22-2015 |
20150300366 | UNIVERSAL HOUSING FOR A CENTRIFUGAL GAS COMPRESSOR - A universal housing for a centrifugal gas compressor is disclosed. The universal housing includes a body, a suction port extending from the body, a discharge port extending from the body, and a first compartment within the body. The first compartment includes a suction inlet in flow communication with the suction port and a discharge outlet in flow communication with the discharge port. The first compartment is configured to receive more than one staging length for the staging. The staging inlet is in flow communication with the suction inlet and the staging outlet is in flow communication with the discharge outlet. | 10-22-2015 |
20150288231 | ELECTRIC MOTOR WITH SYMMETRIC COOLING - An electric motor for a rotary machine is disclosed. The electric motor includes a first lamination section and a second lamination section radially spaced apart from a driver shaft forming a first air gap and a second air gap respectively. The second lamination section is axially spaced apart from the first lamination section forming an air gap cooling outlet there between. The electric motor also includes motor windings extending through the first lamination section and the second lamination section, and across the air gap cooling outlet in circumferential groups. A winding shield is located around each of the circumferential groups of the motor windings. | 10-08-2015 |
20150285253 | PENETRATOR POWER CONNECTOR FOR AN INTEGRATED ROTARY MACHINE - A power connector for an electric motor is disclosed. The power connector includes a flange, a conductor rod, and an insulation sleeve. The conductor rod includes a first portion extending in a first direction from the flange and a second portion extending from the flange in a second direction, opposite the first direction. The second portion includes a lead wire connection end distal to the flange. The insulation sleeve covers the second portion from the flange to the lead wire connection end. The insulation sleeve includes a sleeve outer surface, and a sealing rib extending outward from the sleeve outer surface. | 10-08-2015 |
20150285242 | CONTROLLING A GAS COMPRESSOR HAVING MULTIPLE MAGNETIC BEARINGS - A method for controlling a gas compressor is disclosed. The method includes communicating feedback data about two magnetic bearings to a computer including a multi-core processor via a communication link. The method also includes processing the feedback data about the two magnetic bearings where the feedback data for each of the two magnetic bearings is processed on separate cores of the multi-core processor in parallel and issuing a bearing control command to each of the two magnetic bearings in response to the feedback data. The method further includes communicating the bearing control commands to the two magnetic bearings from the computer via the communication link. | 10-08-2015 |
20150285085 | VARIABLE GUIDE VANE EXTENDED VARIABLE FILLET - A guide vane is disclosed. The guide vane includes a button, a trunnion connected to the button, and an airfoil connected to the button. The airfoil includes an overhang portion wherein the overhang portion extends from one end of the button to a distal end of the airfoil. The guide vane includes a button corner located near the beginning of the overhang portion. The guide vane includes a variable fillet extending into the overhang portion. The variable fillet includes sections of different radiuses along the length of the fillet. | 10-08-2015 |
20150276548 | CONDITION MONITORING AND ANALYTICS FOR MACHINES - A method for monitoring a condition of an actuator for a machine using a closed loop Hammerstein model structure is disclosed. The method includes receiving measured data for the machine and determining an actuator command associated with the measured data. The method also includes identifying a current static nonlinearity using one or more linear regression techniques, where the static nonlinearity is modeled between a known actuator and a linear plant of the machine. The method further includes determining whether the condition of the actuator has changed by comparing a resultant from identifying the current static nonlinearity with information of the known actuator. | 10-01-2015 |
20150262133 | METHOD AND SYSTEM FOR PROVIDING AN ASSESSMENT OF EQUIPMENT IN AN EQUIPMENT FLEET - A method for providing an assessment of equipment in an equipment fleet. The method includes receiving an equipment assessment request. The method also includes transmitting fleet summary information representative of equipment in the equipment fleet. The method also includes receiving an input selecting a piece of equipment from the fleet. The method also includes transmitting equipment summary information representing categories of available summary data for the piece of equipment. The method further includes receiving a second input selecting a category of available summary data. The method further includes transmitting detailed data corresponding to the selected category of available summary data. | 09-17-2015 |
20150253009 | GAS TURBINE ENGINE FUEL INJECTOR WITH AN INNER HEAT SHIELD - A fuel injector for a combustor of a gas turbine engine is disclosed. The fuel injector includes a gas outer tube, a gas inner tube, a liquid tube, and a heat shield. The gas outer tube and the gas inner tube form a gas fuel annulus. The gas inner tube and the liquid tube form a liquid fuel annulus. The liquid tube forms an air cavity. The heat shield extends within the liquid tube forming an insulating gap between the heat shield and the liquid tube. | 09-10-2015 |
20150227657 | POST PROCESSING FINITE ELEMENT ANALYSIS GEOMETRY - A method for designing a component for a circumferential machine is disclosed. The method includes selecting one or more seed nodes, creating a cylindrical coordinate system, and selecting an output subset. The method further includes creating a node set from the one or more seed nodes based on a selected feature of the component to be analyzed. The method yet further includes extracting an output for the node set from the finite element analysis module for each load cycle and presenting a result from the extracted output. | 08-13-2015 |
20150211372 | HOT ISOSTATIC PRESSING TO HEAL WELD CRACKS - A method of manufacturing a shrouded turbine blade is disclosed. In an embodiment, the method comprises casting a shrouded turbine blade including a shrouding. The shrouding includes an abutment face. The method includes welding a coating composed of a different material than the shrouded turbine blade onto the abutment face. The method includes applying hot isostatic pressing to the abutment face after welding the coating. The hot isostatic pressing is sufficient to heal internal defects in the abutment face. The method includes machining the shrouded turbine blade after applying hot isostatic pressing. | 07-30-2015 |
20150204245 | TURBINE BLADE PLATFORM SEAL ASSEMBLY VALIDATION - A platform seal assembly for a gas turbine engine with a turbine disk and a plurality of turbine blades is disclosed. The platform seal assembly includes a platform seal and a validation tab. The platform seal includes a first end, a second end, opposite and distal to the first end, and a body extending between the first end and the second end. The validation tab includes an attachment portion affixed to the platform seal and an observable indicator portion extending from the attachment portion. | 07-23-2015 |
20150198333 | FUEL INJECTOR WITH A DIFFUSING MAIN GAS PASSAGE - A fuel injector for a combustor of a gas turbine engine is disclosed. The fuel injector includes a gas gallery and a gas passage. The gas gallery is an annular passage configured to circumferentially distribute gas fuel. The gas passage includes an inlet and an outlet. The inlet is distal to the gas gallery and includes an inlet area with a circular shape. The outlet adjoins the gas gallery and includes an outlet area including an annular sector shape. The gas passage is configured to diffuse the gas fuel and discharge the gas fuel from the outlet and into the gas gallery. | 07-16-2015 |
20150198169 | SYNTHETIC JETS IN COMPRESSORS - A synthetic jet for a stationary vane for a turbo-machine is disclosed. The synthetic jet includes a backside cavity and a jet cavity. The jet cavity includes a frontside cavity adjoining the backside cavity and a jet passage extending from a fluid stream interfacing surface of the airfoil towards the frontside cavity. The jet passage is in flow communication with the frontside cavity. The synthetic jet also includes a disk located between the backside cavity and the frontside cavity. The disk includes a cylindrical disk and a coating on each side of the cylindrical disk. The coating is a piezo electric ceramic material. | 07-16-2015 |
20150198094 | CERAMIC PEDESTAL AND SHIELD FOR GAS PATH TEMPERATURE MEASUREMENT - A mounting stand for a temperature sensor is disclosed. The mounting stand includes a base, a pedestal, and a shield. The pedestal extends from the base to a pedestal end distal to the base. The pedestal includes a first hollow cylinder shape forming a bore there through. The shield includes a second hollow cylinder shape extending from the base about the pedestal and extending beyond the pedestal to a shield end distal to the base forming a flow region between the pedestal and the shield. The shield also includes a first aspiration hole extending through the second hollow cylinder shape. | 07-16-2015 |
20150198053 | GAS TURBINE ENGINE WITH EXIT FLOW DISCOURAGER - A turbine stage for a gas turbine engine is disclosed. The turbine stage includes a turbine disk and a turbine diaphragm, forming a cavity there between. The turbine stage also includes an exit flow discourager comprised of at least two teeth. The teeth may be located radially apart from each other, each tooth including a length extending in the axial direction and a width extending in the radial direction. A channel is formed between the teeth and an axially adjacent surface. A recirculation region may be formed in between each pair of teeth. | 07-16-2015 |
20150184516 | NOZZLE ENDWALL FILM COOLING WITH AIRFOIL COOLING HOLES - A nozzle segment for a nozzle ring of a gas turbine engine is disclosed. The nozzle segment includes an upper endwall, a lower endwall, and an airfoil extending between the upper endwall and the lower endwall. The airfoil includes a pressure side wall, a plurality of inner cooling apertures, and a plurality of outer cooling apertures. The plurality of inner cooling apertures extends through a pressure side wall and is arranged in a first row adjacent the lower endwall. The plurality of outer cooling apertures extends through the pressure side wall and is arranged in a second row adjacent the upper endwall. | 07-02-2015 |
20150105966 | CONDITION BASED LIFING OF GAS TURBINE ENGINE COMPONENTS - A system and methods for the condition based lifing of a gas turbine engine component is disclosed. The system and methods determine the stress and caused by fatigue and creep for each load cycle of the gas turbine engine, and use a ductility exhaustion method to combine the fatigue and creep strain rates determined from the fatigue and creep stresses to determine the remaining useful of the gas turbine engine component. | 04-16-2015 |
20150104335 | INTERNAL-DRIVEN COMPRESSOR HAVING A POWERED COMPRESSOR ROTOR - The internal-driven compressor having a powered compressor rotor. The internal-driven compressor includes a compressor housing including a suction port and a discharge port, an internal driver including a rotor and a stator, the rotor and the stator located within the compressor housing, the stator located radially inward of the rotor, and a powered compressor rotor including an annular body extending about a center axis, wherein the rotor is fixed to the powered compressor rotor and configured to rotate the powered compressor rotor about the center axis in response to a force imparted by the stator. | 04-16-2015 |
20150075131 | EXHAUST COLLECTOR WITH CURVED SIDE PANEL - An exhaust collector for a gas turbine engine is disclosed. The exhaust collector includes a front panel, a rear panel, and a side panel. The side panel includes a circumferential portion, a first contoured portion, and a second contoured portion. The circumferential portion extends about the exhaust collector axis with a constant radius. The first contoured portion and the second contoured portion are each between the circumferential portion and the exhaust outlet and include a plurality of curved sections with alternating concavity. Each of the plurality of curved sections extends from the front panel to the rear panel. | 03-19-2015 |
20150053750 | HIGH TEMPERATURE BRAZING FIXTURE AND METHOD OF MANUFACTURE - A high temperature brazing fixture and method of manufacture for a gas turbine component made of a superalloy is disclosed herein. The high temperature brazing fixture includes a first and second frame member, a support member, and positioning member, all of which are made from the superalloy and fastened together using tab and tab lock couplings. The support member is configured to interface with and support the gas turbine engine component, and the positioning member is configured to interface with and position at least a first location of or hold a first dimension of the gas turbine component. | 02-26-2015 |
20150052909 | FUEL CONTROL MODULE GAS VENT MANIFOLD - A fuel control module including a gas vent manifold is disclosed. The gas vent manifold includes a first gas vent portion including a first gas vent connection and a second gas vent portion including a second gas vent connection. The gas vent manifold also includes a condensation portion extending between the first gas vent portion and the second gas vent portion. The gas vent manifold further includes a condensation drain port fluidly connected to the condensation portion. The gas vent manifold also includes a plurality of connection ports. Each connection port is configured to fluidly couple the gas vent manifold to a vent line of one or more pneumatic valves. | 02-26-2015 |
20150046126 | GAS TURBINE ENGINE ROTOR ASSEMBLY OPTIMIZATION - A method for optimizing a rotor assembly for a gas turbine engine is disclosed. The rotor assembly includes rotating parts including a first journal and one or more rotor disks. The method includes determining vector components for a total parallelism vector for each rotating part, determining a total parallelism sum including determining a magnitude of each total parallelism vector and adding the magnitudes into a single sum, and determining a minimum value for the total parallelism sum including selecting the rotor disk build angles and the second journal build angle that result in the smallest value for the total parallelism sum. | 02-12-2015 |
20150044035 | HIGH POROSITY ABRADABLE COATING - An abradable coating for a gas turbine engine includes a bond coat, an intermediate layer, and a porous layer. The bond coat includes a metal coating and a thickness from 0.152 millimeters to 0.229 millimeters. The intermediate layer includes a ceramic material and a thickness from 0.051 millimeters to 0.381 millimeters. The porous layer includes a porous ceramic material. The porous layer also includes a porosity greater than thirty-five percent of a volume of the porous layer. The porous layer further includes a thickness from 0.127 millimeters to 1.524 millimeters. | 02-12-2015 |
20150033746 | HEAT SHIELD WITH STANDOFFS - A heat shield for a combustion chamber of a gas turbine engine is disclosed. The heat shield includes a plate portion, an inner ring, and a plurality of standoffs. The plate portion includes an annular sector shape. The inner ring extends from an inner part of the plate portion. The inner ring includes a hollow cylinder shape. The plurality of standoffs extends from the plate portion, proximate outer edges of the plate portion and in the same direction as the inner ring. The plurality of standoffs forms a plurality of scallops. Each scallop is located between adjacent standoffs. | 02-05-2015 |
20150030428 | METHOD FOR ENHANCING POWER OF A GAS TURBINE ENGINE - A method for servicing a gas turbine engine to enhance the power output of the gas turbine engine including a control system, inlet guide vanes, and a third stage power turbine nozzle is disclosed. The control system includes an inlet guide vane module. The method includes increasing an operating range of each inlet guide vane to at least 62 degrees. The method also includes modifying a total flow area of the third stage power turbine nozzle by 2% to 12%, the total flow area including flow areas between adjacent airfoils in the third stage power turbine nozzle. | 01-29-2015 |
20140354287 | APPARATUS FOR TESTING AN ELECTROMECHANICAL RELAY - A portable apparatus for testing an electromechanical relay having Normally Closed (NC) contacts, Normally Open (NO) contacts, and an electromagnetic coil therein includes a housing, a battery, a battery test circuit, and a relay test circuit. The battery test circuit includes a first switch operable to provide a first type of indication based on a voltage output by the battery. The relay test circuit includes a second switch, and a third switch. The second switch is operable to provide a second type of indication if an electrical circuit of the relay test circuit is complete with the NC contacts of the relay. The third switch is operable to energize the electromagnetic coil and provide the second type of indication if NO contacts of the relay become closed upon energizing the electromagnetic coil, thus opening the NC contacts of the relay. | 12-04-2014 |
20140348647 | EXHAUST DIFFUSER FOR A GAS TURBINE ENGINE EXHAUST SYSTEM - An exhaust diffuser for a gas turbine engine includes a diffuser inlet, a diffuser exit, an inner diffuser wall, and an outer diffuser wall. The inner diffuser wall may include a first tubular member with a flared downstream portion. The outer diffuser wall may include a second tubular member at least partially about the inner diffuser wall and with a second flared downstream portion. The outer diffuser wall and the inner diffuser wall extend between the diffuser inlet and the diffuser exit, and form a diffusing flowpath therebetween. The second flared downstream portion may include a lower section and an upper section, with the upper section extending further downstream in an axial direction than the lower section, relative to the diffuser axis. | 11-27-2014 |
20140338341 | LIQUID FUEL TURBINE ENGINE FOR REDUCED OSCILLATIONS - A gas turbine engine may include a plurality of pilot fuel supply lines configured to supply liquid fuel. Each pilot fuel supply line may be coupled to a respective fuel injector. The turbine engine may include a plurality of main fuel supply lines configured to supply liquid fuel. Each main fuel supply line may be coupled to a respective fuel injector. The turbine engine may also include a flow restriction provided in a first plurality of the plurality of main fuel supply lines. A second plurality of the plurality of main fuel supply lines may be free from the flow restriction. | 11-20-2014 |
20140332603 | SHROUDED PILOT LIQUID TUBE - A pilot liquid tube having a pilot liquid fuel inlet, a pilot liquid fuel conduit, a pilot liquid fuel nozzle, and a shroud configured to shield the pilot liquid fuel nozzle. The pilot liquid tube may be installed and/or removed from an injector of a gas turbine engine while the shroud remains fixed to pilot liquid fuel conduit. | 11-13-2014 |
20140332602 | INNER PREMIX TUBE AIR WIPE - An inner premix tube for a fuel injector of a gas turbine engine includes a transition end, a tip end, and a premix tube inner surface. The transition end includes an annular disk portion with an annular disk shape and a redirection portion extending radially inward and axially from the annular disk portion. The transition end also includes a plurality of wipe passages extending through the transition end. The tip end includes a cylindrical portion with a hollow right circular cylinder shape. The premix tube inner surface is a radially outer surface including the redirection portion outer surface and the cylindrical portion outer surface. | 11-13-2014 |
20140331678 | SYSTEM FOR DISTRIBUTING COMPRESSED AIR IN A COMBUSTOR - A system for distributing compressed air in a combustor of a gas turbine engine. The system may include a flow splitter, a center duct, an outer duct, and an inner duct configured to separate and receive compressed air from a prediffuser exit, and to route separate flows of the compressed air to separate downstream locations for the combustion reaction and for cooling. The system may include an axial mixer configured to axially receive a flow of the compressed air and to direct the flow to mix with fuel provided by an injector. | 11-13-2014 |
20140331677 | OUTER PREMIX BARREL VENT AIR SWEEP - A gas turbine engine outer premix barrel is disclosed. The outer premix barrel includes a body portion, a barrel portion, and a plurality of vanes. The body portion includes vent air inlets. The barrel portion extends axially aft from the body portion. The plurality of vanes extends axially forward from the body portion. Each vane includes an inward surface located at a radially inner end of the vane, and a plurality of vent passages exiting the vane at the inward surface. Each vent passage is in flow communication with at least one vent air inlet. | 11-13-2014 |
20140331676 | TAPERED GAS TURBINE ENGINE LIQUID GALLERY - A liquid gallery for a fuel injector of a gas turbine engine includes a gallery body, a liquid gallery scroll, a plurality of atomizer inlets, and a plurality of atomizer bosses. The liquid gallery scroll extends into the gallery body spanning from a first end to a second end in a circumferential direction. The liquid gallery scroll includes a taper with a cross-sectional area of the liquid gallery scroll reducing from the first end to the second end. Each atomizer inlet is in flow communication with the liquid gallery scroll. Each atomizer boss is aligned with one of the plurality of atomizer inlets. | 11-13-2014 |
20140331675 | PIVOTING SWIRLER INLET VALVE PLATE - A swirler inlet valve plate for a fuel injector of a gas turbine engine includes a blocker ring and a pivot sleeve mechanically connected to the blocker ring. The blocker ring is formed from at least a portion of a toroid shape. The blocker ring includes a blocking surface perpendicular to an axis of the blocker ring formed from at least a portion of an annulus. The blocker ring also includes a flow surface, an inner circumferential surface of the toroidal shape. The pivot sleeve includes a sleeve portion extending adjacent the blocker ring. The sleeve portion includes a rotation transmission mechanism. | 11-13-2014 |
20140303780 | METHOD FOR CONTROLLING A GAS COMPRESSOR HAVING A MAGNETIC BEARING - A method for controlling a gas compressor having a magnetic bearing. The method includes communicating digital feedback data from a magnetic bearing system to a computer via a communication link, processing the feedback data with the computer and issuing a bearing control command in response to the feedback data, communicating the bearing control command from the computer to the magnetic bearing system via a communication link, providing operational processing and control of the gas compressor with the computer, and providing operational processing and control of the compressor driver with the computer. | 10-09-2014 |
20140303779 | CONTROL SYSTEM FOR MAGNETIC BEARINGS IN A CENTRIFUGAL GAS COMPRESSOR - A control system and method of control for a centrifugal gas compressor including a magnetic bearing. The control system and method is configured to control the operation of a magnetic bearing system, and may control other systems of the gas compressor as well. Bearing communications are digitized proximate the gas compressor and communicated using data packet communications. The compressor and magnetic bearing controls may be performed on the same computer, and the control systems of the compressor, magnetic bearing, and engine or motor can all share information, a common user interface, and a common uninterrupted power source. | 10-09-2014 |
20140294559 | MULTIPLE MODE GAS TURBINE ENGINE GAS FUEL SYSTEM WITH INTEGRATED CONTROL - A method for operating a gas turbine engine is disclosed. The method includes determining whether the gas turbine engine fuel system is in a steady state mode or a transient mode. The method also includes modifying the gas turbine engine power output by modifying a pressure set point of the fuel system while maintaining a fuel control valve in a steady state when in the steady state mode. The method further includes modifying the gas turbine engine output by modifying the position of the fuel control valve while maintaining the pressure set point of the fuel system constant when in the transient mode. | 10-02-2014 |
20140290262 | LOW FLOW CORRECTION FOR GAS TURBINE ENGINE FUEL VALVE CHARACTERISTICS - A method for controlling a gas turbine engine fuel control valve during low flow conditions includes positioning the fuel control valve in an operating position. The method also includes determining a fuel control valve flow sensor flow rate while in the operating position and determining a corrected effective flow area (“Cda”) of the fuel control valve. The method further includes generating Cda versus command data with the corrected Cda and the operating position and inserting the generated Cda versus command data into the nominal Cda versus command data set when nominal Cda versus command data is not known at the operating position. | 10-02-2014 |
20140290261 | COMPENSATION FOR GAS TURBINE ENGINE FUEL VALVE CHARACTERISTICS - A method for operating a gas turbine engine fuel system with a fuel control valve is disclosed. The method includes metering fuel through the fuel control valve with an effective flow area versus command data set. The method also includes detecting that a change in an effective flow area of the fuel control valve has occurred. The method further includes modifying the effective flow area versus command data set to reflect the detected change in the effective flow area of the fuel control valve. | 10-02-2014 |
20140286782 | TURBINE BLADE STAKING PIN - A staking pin for a gas turbine engine is disclosed. The staking pin may include a solid portion extending part of a length of the staking pin, and a hollow portion extending an additional part of the length of the staking pin. The staking pin may be constructed of Alloy X material having an average grain diameter of between about 0.0449 and 0.1270 mm. | 09-25-2014 |
20140271206 | TURBINE BLADE WITH A PIN SEAL SLOT - A gas turbine engine turbine disk assembly includes a turbine disk, turbine blades, and pin seals. Each turbine blade includes a platform with a pressure side seal slot extending into a pressure side of the platform and a suction side seal slot extending into a suction side of the platform. The pressure side seal slot and the suction side seal slot are each angled between three and ten degrees in the radial direction relative to the axis of the turbine disk. The pin seal includes a cylindrical shape and is located within a seal slot formed from the pressure side seal slot and the suction side seal slot of adjacent turbine blades. | 09-18-2014 |
20140271205 | TURBINE BLADE PIN SEAL - A gas turbine engine turbine disk assembly includes a turbine disk, turbine blades, and pin seals. Each turbine blade includes a platform with a pressure side seal slot extending into a pressure side of the platform and a suction side seal slot extending into a suction side of the platform. The pressure side seal slot and the suction side seal slot are each angled between three and ten degrees in the radial direction relative to the axis of the turbine disk. The pin seal includes a cylindrical shape and is located within a seal slot formed from the pressure side seal slot and the suction side seal slot of adjacent turbine blades. | 09-18-2014 |
20140260572 | Sensor Housing - A sensor housing is provided. The sensor housing includes an elongated body having an open end and a closed end. An opening is disposed axially within the elongated body through the open end and is configured to receive a sensor secured therein. A support section is connected to the closed end of the elongated body and coupled to a receiving port disposed on the gas turbine engine system. The elongated body has an axial dimension determined according to a vibration characteristic of the gas turbine engine system during operation. | 09-18-2014 |
20140259598 | ANALYSIS OF LOCALIZED WASTE MATERIAL - A testing method for a component is provided. The method identifies a flaw region of the component. The flaw region is prone to defects. The method then isolates a waste material associated with the identified flaw region. The method analyzes the isolated waste material for an undesirable microstructure associated with defects. Subsequently, the method determines rejection and acceptance of the component based, at least in part, on the analysis. | 09-18-2014 |
20140250916 | SYSTEM AND METHOD FOR ALIGNING A GAS TURBINE ENGINE - A system and method for aligning a gas turbine engine. The system and method includes installing an alignment mount, determining whether the gas turbine engine is aligned and/or in a sufficiently aligned condition, and modifying a vertical position of the gas turbine engine at the alignment mount in response. The alignment mount includes an engine attachment, a ground attachment, and an expansion member configured to allow the engine attachment and the ground attachment to move relative to each other and maintain a load path therebetween. | 09-11-2014 |
20140250907 | GAS TURBINE FUEL INJECTOR WITH METERING CAVITY - A fuel injector for a gas turbine engine may include a flow path for a fuel-air mixture extending longitudinally through the fuel injector, and a fuel gallery extending circumferentially around the flow path. The fuel gallery may be adapted to inject a liquid fuel into the flow path. The fuel injector may also include an annular casing positioned circumferentially around the fuel gallery to define an insulating chamber around the gallery. The fuel injector may also include an annular cover extending around the fuel injector to define a metering chamber. The fuel injector may further include one or more purge holes fluidly coupling the metering chamber to the insulating chamber, and one or more metering holes fluidly coupling the metering chamber to a volume exterior to the fuel injector. | 09-11-2014 |
20140244518 | AMBIENT CONDITIONS MONITORING SYSTEM FOR MACHINERY - A method for monitoring machines is provided. According to the method, a computer server determines a location of at least one machine. The complier server transmits a request to an external source for ambient conditions associated with the location of the at least one machine. The computer server receives a response indicative of the ambient conditions associated with the location of the at least one machine. In addition, the computer server evaluates operation of the at least one machine based in part on the received ambient conditions. | 08-28-2014 |
20140209124 | GAS TURBINE OFFLINE COMPRESSOR WASH WITH BUFFER AIR FROM COMBUSTOR - A system and method for washing a gas turbine engine. The method for washing the gas turbine engine includes coupling a pressurized air supply assembly to an air supply and to a secondary air system, cranking a compressor rotor assembly of the gas turbine engine, supplying pressurized offline buffer air from the air supply to the pressurized air supply assembly, and spraying a cleaner into the compressor. | 07-31-2014 |
20140209123 | COMPRESSOR WASH WITH AIR TO TURBINE COOLING PASSAGES - A system and method for washing a gas turbine engine. The method for washing the gas turbine engine includes coupling a pressurized air supply assembly to an air supply and to a secondary air system, cranking a compressor rotor assembly of the gas turbine engine, supplying pressurized offline buffer air from the air supply to the pressurized air supply assembly, and spraying a cleaner into the compressor. | 07-31-2014 |
20140208762 | COMPRESSOR WASH WITH AIR TO BEARING BUFFERING SYSTEM - A system and method for washing a gas turbine engine. The method for washing the gas turbine engine includes coupling a pressurized air supply assembly to an air supply and to a secondary air system, cranking a compressor rotor assembly of the gas turbine engine, supplying pressurized offline buffer air from the air supply to the pressurized air supply assembly, and spraying a cleaner into the compressor. | 07-31-2014 |
20140178203 | COATING FIXTURES FOR GAS TURBINE ENGINE COMPRESSOR DISKS - A method for coating a gas turbine engine compressor rotor having a compressor disk with axial slots includes inserting masking fixtures into the axial slots. Each masking fixture includes a masking root that matches the shape of a blade root of an axial blade configured to be inserted into the axial slot the masking fixture is inserted into. The method also includes applying a coating to the compressor rotor after inserting the masking fixtures into the axial slots followed by drying the coating on the compressor rotor at a predetermined temperature. The method further includes removing the masking fixtures from the axial slots after drying the coating on the compressor rotor followed by curing the coating on the compressor rotor. | 06-26-2014 |
20140175208 | PORTABLE TUBE COILER - A portable tube coiler and method for coiling. The portable tube coiler includes a spool assembly having a rotation axis and including a spool configured to rotate about the rotation axis ( | 06-26-2014 |
20140174093 | GAS TURBINE ENGINE LUBE OIL SYSTEM - A gas turbine engine lube oil system ( | 06-26-2014 |
20140165592 | COMPRESSOR BLADE FOR GAS TURBINE ENGINE - A compressor blade for a gas turbine engine is disclosed. The compressor blade may have a root configured to engage a hub of the gas turbine engine, and an airfoil radially extending a distance from the root to a tip. The airfoil may have a suction side, a pressure side, a leading edge connecting the suction and pressure sides, and a trailing edge connecting the suction and pressure sides opposite the leading edge. The distance that the airfoil extends from the root to the tip may be divided into a plurality of radially adjacent regions. At least one, but not all, of the plurality of radially adjacent regions away from the base and the tip may have a substantially constant thickness. | 06-19-2014 |
20140165583 | BLEED VALVE OVERRIDE SCHEDULE ON OFF-LOAD TRANSIENTS - In one aspect, the present disclosure is directed to a method for controlling a position of a bleed valve of a gas turbine engine. The onset of an off-load transient may be determined. Values representative of the turbine rotor inlet temperature and the exhaust outlet temperature may be determined. Also, the amount of time elapsed since the onset of the off-load transient may be determined. Three provisional bleed valve command positions may be determined based on value representative of the turbine rotor inlet temperature, the value representative of the exhaust outlet temperature, and the amount of time elapsed, respectively. The provisional bleed valve command position associated with the lowest relative value may be selected. Then, the bleed valve position may be adjusted to match the selected bleed valve command position. | 06-19-2014 |
20140157784 | SPLIT FUEL CONTROL MODULE - A split fuel control module for a gas turbine engine and method of installation. The split fuel control module includes a first frame unit, a second frame unit, a segmented fuel path, and a distributed fuel controller. The first frame unit and the second frame unit are joined together at a frame unit interface. The segmented fuel path includes an upstream fuel interface fixed to the first frame unit and a downstream fuel interface fixed to the second frame unit and detachably coupled to the upstream fuel interface at the frame unit interface. A first portion of the distributed fuel controller is fixed to the first frame unit, and a second portion of the distributed fuel controller is fixed to the second frame unit. | 06-12-2014 |
20140157780 | FUEL CONTROL MODULE - A fuel control module for a gas turbine engine and method of installation. The fuel control module includes a first frame unit, a second frame unit, a fuel path, and a fuel controller components. The first frame unit and the second frame unit include features for installation in multiple installations and/or multiple configurations. | 06-12-2014 |
20140157596 | FREE-STATE SEAL PLATE FUNCTIONAL GAGE TOOL - A gage tool ( | 06-12-2014 |
20140157569 | METHOD OF INSTALLING SPLIT FUEL CONTROL MODULE - A split fuel control module for a gas turbine engine and method of installation. The split fuel control module includes a first frame unit, a second frame unit, a segmented fuel path, and a distributed fuel controller. The first frame unit and the second frame unit are joined together at a frame unit interface. The segmented fuel path includes an upstream fuel interface fixed to the first frame unit and a downstream fuel interface fixed to the second frame unit and detachably coupled to the upstream fuel interface at the frame unit interface. A first portion of the distributed fuel controller is fixed to the first frame unit, and a second portion of the distributed fuel controller is fixed to the second frame unit. | 06-12-2014 |
20140156242 | METHOD AND SYSTEM FOR AUTOMATED MACHINE DESIGN - A system for automated machine design is disclosed. The system may have at least one of a part database and a relationship database, a display device, and an input device. The system may also have one or more processors in communication with the at least one of a part database and a relationship database, the display device, and the input device. The processors may be configured to cause a listing of components selectable by a customer for inclusion within a machine to be shown on the display device, and to receive a selection of the components from the listing by the customer via the input device. The processors may also be configured to retrieve data regarding selected components from the at least one of the part database and the relationship database, and to generate a design for at least one new support component in the machine based on the selected components and the data. | 06-05-2014 |
20140154046 | VARIABLE AREA TURBINE NOZZLE WITH A POSITION SELECTOR - A gas turbine engine ( | 06-05-2014 |
20140150454 | TURBINE BLADE APPARATUS - A turbine blade is disclosed. The turbine blade may include a platform, an airfoil extending from one side of the platform, and a neck extending from another side of the platform, wherein the neck includes a forward buttress and an aft buttress. The turbine blade may further include a root extending from the neck, a pocket defined by a plurality of walls and located between the forward. buttress and the aft buttress, and a variable radius fillet. The variable radius fillet may be disposed within the pocket and extend between the forward buttress and the aft buttress, wherein a radius of the variable radius fillet increases from the forward buttress to the aft buttress. | 06-05-2014 |
20140147259 | GAS TURBINE ENGINE TURBINE NOZZLE IMPINGEMENT COVER - An impingement cover ( | 05-29-2014 |
20140144140 | FUEL BOOST MODULE - A fuel boost module for a gas turbine engine having a base, a fuel inlet configured to receive fuel from a fuel supply, a fuel outlet configured to deliver fuel to the gas turbine engine, a filter assembly configured to filter the fuel, a fuel controller configured to regulate pressure of the fuel that will be delivered to the gas turbine engine, a boost pump configured to pressurize the fuel, and a main pump configured to pressurize the fuel. | 05-29-2014 |
20140140849 | GAS TURBINE ENGINE COMPRESSOR ROTOR ASSEMBLY AND BALANCING SYSTEM - A method for balancing a compressor rotor assembly including a forward weldment ( | 05-22-2014 |
20140137488 | ENGINE ENCLOSURE WITH PANEL RETAINER ASSEMBLIES - An engine enclosure includes a frame, multiple roof panels, and multiple retainer assemblies. The roof panels are disposed on the frame and include one or more threaded receptacles. The retainer assemblies are configured to releasably secure the roof panels to the frame. The retainer assemblies include a clamp, and a threaded fastener. The clamp includes a first portion and a second portion. The first portion is disposed adjacent to the frame. The second portion is substantially offset from the first portion and includes an aperture. The threaded fastener is disposed within the aperture and releasably fastened to the threaded receptacle. | 05-22-2014 |
20140125791 | COMBUSTOR IMAGING INSPECTION SYSTEM - An imaging inspection system and inspection method for a combustion chamber of a gas turbine engine having an imaging inspection device and a controller. The imaging inspection device includes a combustor interface, an inspection head having a first camera, an inspection head extender, a roll actuator, and a pitch actuator. The controller is configured to manipulate the inspection head in a predefined sequence. | 05-08-2014 |
20140119943 | TURBINE ROTOR ASSEMBLY - A turbine rotor assembly may include a turbine rotor with a plurality of turbine blade slots and a plurality of turbine blades. A root structure of each turbine blade may include a portion shaped to be received in a corresponding turbine blade slot of the rotor. The rotor assembly may also include a seal plate attached to the forward end of the rotor. The seal plate may extend upwards from a first end below the inner end of the blade slots to a second end located between an outermost lobe of the blade slots and the outer rim of the rotor. | 05-01-2014 |
20140119918 | DAMPER FOR A TURBINE ROTOR ASSEMBLY - A damper for a turbine rotor assembly of a gas turbine engine may include a forward plate including a forward face and an aft face, and an aft plate including a forward face and an aft face. The aft face of the forward plate may he connected to the forward face of the aft plate with a longitudinal structure. An area of the aft plate in a plane transverse to the longitudinal structure may be larger than an area of the forward plate in the plane transverse to the longitudinal structure. The damper may also include a nub projecting from a lower portion of the aft face of the aft plate. | 05-01-2014 |
20140119917 | TURBINE BLADE FOR A GAS TURBINE ENGINE - A turbine blade for a gas turbine engine may include a platform, an airfoil extending above the platform, and a root structure extending below the platform. The root structure may extend from a forward face to an aft face and include a shank region proximate the platform and a lower portion distal to the platform. The forward face of the shank region may project outward from the forward face of the lower portion. | 05-01-2014 |
20140119916 | DAMPER FOR A TURBINE ROTOR ASSEMBLY - A damper for a turbine rotor assembly of a gas turbine engine may include a forward plate with a forward face and an aft face, and an aft plate with a forward face and an aft face. The aft face of the forward plate may be connected to the forward face of the aft plate with a longitudinal structure. An area of the aft plate in a plane transverse to the longitudinal structure may be greater than an area of the forward plate in the plane transverse to the longitudinal structure. The damper may also include a pocket on the forward face of the forward plate. | 05-01-2014 |
20140119895 | GAS TURBINE ENGINE COMPRESSOR WITH A BIASED INNER RING - An inner bushing assembly ( | 05-01-2014 |
20140119894 | VARIABLE AREA TURBINE NOZZLE - A gas-turbine engine ( | 05-01-2014 |
20140116056 | GAS TURBINE DIFFUSER WITH FLOW SEPARATOR - A diffuser for use in a gas turbine engine, the diffuser having a first wall, a second wall, and a flow separator. The first and second wall define an annular cavity, with the annular cavity having an inlet. The first and second wall also forming a prediffuser that is proximate the inlet, and a dump region distal the inlet. The flow separator extends from the first wall into the annular cavity. | 05-01-2014 |
20140112774 | CENTRIFUGAL GAS COMPRESSOR MAGNETIC BEARING THRUST COLLAR WITH MOUNTING PILOTS - A thrust collar ( | 04-24-2014 |
20140112773 | CENTRIFUGAL GAS COMPRESSOR WITH A HARDENED SHAFT FOR A BEARING SYSTEM | 04-24-2014 |
20140103846 | SYSTEM AND METHOD FOR CONTROLLING AN ELECTRIC MOTOR - A system for controlling an electric motor is disclosed herein. In particular, the system receives a user input indicative of a desired performance parameter for the electric motor. Based on the desired performance parameter, the system determines a control parameter that defines an operational range. The system then adjusts the electric motor according to the control parameter so that the electric motor generates constant output power over the operational range. | 04-17-2014 |
20140099190 | GAS TURBINE ENGINE TURBINE HOUSING WITH ENLONGATED HOLES - A turbine housing ( | 04-10-2014 |
20140093391 | COOLED TURBINE BLADE WITH TRAILING EDGE FLOW METERING - A cooled turbine blade having a base and an airfoil, the base including cooling air inlet and an internal cooling air passageway, and the airfoil including an internal heat exchange path beginning at the base and ending at a cooling air outlet at the trailing edge of the airfoil. The airfoil also includes a “skin” that encompasses a tip wall, an inner spar, a plurality of trailing edge cooling fins, and a perforated first and second trailing edge rib configured to meter cooling air passing there thorough. | 04-03-2014 |
20140093390 | COOLED TURBINE BLADE WITH LEADING EDGE FLOW REDIRECTION AND DIFFUSION - A cooled turbine blade having a base and an airfoil, the base including cooling air inlet and an internal cooling air passageway, and the airfoil including an internal heat exchange path beginning at the base and ending at a cooling air outlet at the trailing edge of the airfoil. The airfoil also includes a “skin” that encompasses a tip wall, an inner spar, a leading edge rib, and a leading edge air deflector. The leading edge rib is configured to form a leading edge chamber in conjunction with the leading edge of the skin. The leading edge air deflector is shaped and positioned such that cooling air leaving the leading edge chamber is both turned and diffused. | 04-03-2014 |
20140093388 | COOLED TURBINE BLADE WITH LEADING EDGE FLOW DEFLECTION AND DIVISION - A cooled turbine blade having a base and an airfoil, the base including cooling air inlet and an internal cooling air passageway, and the airfoil including an internal heat exchange path beginning at the base and ending at a cooling air outlet at the trailing edge of the airfoil. The airfoil also includes a “skin” that encompasses a tip wall, an inner spar, a leading edge rib, and a leading edge air deflector. The leading edge rib is configured to form a leading edge chamber in conjunction with the leading edge of the skin. The leading edge air deflector is at least partially intersected by the inner spar. | 04-03-2014 |
20140093387 | METHOD OF MANUFACTURING A COOLED TURBINE BLADE WITH DENSE COOLING FIN ARRAY - A method of manufacturing a cooled turbine blade for use in a gas turbine engine. The method includes forming an inner blade pattern, the inner blade pattern including an inner spar and a plurality of inner spar cooling fins. The method also includes forming an inner blade core, removing the inner blade pattern from the inner blade core, forming an outer blade pattern, forming a casting shell, removing the outer blade pattern from the casting shell, and casting the cooled turbine blade in the casting shell. The method also includes removing the casting shell from the cast cooled turbine blade, and removing the inner blade core from the cast cooled turbine blade. | 04-03-2014 |
20140093386 | COOLED TURBINE BLADE WITH INNER SPAR - A cooled turbine blade having a base and an airfoil, the base including cooling air inlet and an internal cooling air passageway, and the airfoil including an internal heat exchange path beginning at the base and ending at a cooling air outlet at the trailing edge of the airfoil. The airfoil also includes a “skin” that encompasses a tip wall, an inner spar, a plurality of inner spar cooling fins extending from the inner spar to the skin, and a plurality of trailing edge cooling fins extending from the pressure side of the skin to the lift side of the skin aft of the inner spar. | 04-03-2014 |
20140086727 | GAS TURBINE ENGINE TURBINE DIAPHRAGM WITH ANGLED HOLES - A gas turbine engine turbine diaphragm ( | 03-27-2014 |
20140083101 | GAS TURBINE ENGINE PRESWIRLER WITH ANGLED HOLES - A gas turbine engine preswirler ( | 03-27-2014 |
20140064946 | GAS TURBINE ENGINE COMPRESSOR UNDERCUT SPACER - A gas turbine engine compressor spacer ( | 03-06-2014 |
20140047813 | EXHAUST COLLECTOR WITH RADIAL AND CIRCUMFERENTIAL FLOW BREAKS - An exhaust collector having a radial inlet configured to receive exhaust gas in a radial direction, an outlet configured to deliver exhaust gas in and outlet direction, and an enclosure configured to collect the received exhaust gas into at least two circumferential counter flows, and route the collected exhaust gas to the outlet, wherein the enclosure includes a collected flow barrier configured to divide the collected exhaust gas from the exhaust gas received at the radial inlet, and a collected flow circumferential divider configured to form a physical barrier between at least a portion of the at least two circumferential counter flows. | 02-20-2014 |
20140026999 | EXHAUST DIFFUSER FOR A GAS TURBINE ENGINE HAVING CURVED AND OFFSET STRUTS - An exhaust diffuser having an outer turbine mounting interface, an outer exhaust collector mounting interface, an outer diffuser wall extending between the outer turbine mounting interface and the outer exhaust collector mounting interface, an inner turbine mounting interface, an inner exhaust collector mounting interface, an inner diffuser wall extending between the inner turbine mounting interface and the inner exhaust collector mounting interface, and a plurality of struts circumferentially distributed around the center axis and extending between the outer diffuser wall and the inner diffuser wall, wherein each of the plurality of struts is radially curved between the diffuser flow outer wall and the diffuser flow inner wall, respectively, and wherein the termination points of each strut is outer wall interface are radially offset from each other. | 01-30-2014 |
20140023504 | FIRST STAGE COMPRESSOR DISK CONFIGURED FOR BALANCING THE COMPRESSOR ROTOR ASSEMBLY - A first stage compressor disk of a gas turbine engine includes a body. The body includes a forward end, an aft end, and an outer surface. The body also includes a plurality of forward balancing holes through the outer surface. The forward balancing holes align circumferentially about the body. The body further includes a plurality of aft balancing holes through the outer surface. The aft balancing holes align circumferentially about the body and are located aft of the forward balancing holes. The first stage compressor disk also includes a radial flange at the aft end of the body. The radial flange extends radially outward from the body. The radial flange includes slots for mounting airfoils. | 01-23-2014 |
20140017078 | AUXILIARY BEARING LANDING GUARD - Radial magnetic bearings ( | 01-16-2014 |
20140015361 | LAMINATION SLEEVE WITH AN AXIAL HYDRAULIC FITTING PORT - A centrifugal gas compressor radial magnetic bearing ( | 01-16-2014 |
20140010634 | PRESWIRLER CONFIGURED FOR IMPROVED SEALING - A preswirler of a gas turbine engine includes an outer ring. The outer ring includes an outer flange with a plurality of first holes, and an outer cylindrical portion extending from the outer flange. The preswirler also includes an inner ring. The inner ring includes an inner flange spaced apart from the outer flange. The inner ring also includes an inner cylindrical portion located within the outer cylindrical portion and a back portion extending from the inner flange to the inner cylindrical portion. The inner ring further includes a plurality of second holes. | 01-09-2014 |
20140001335 | TURBINE ENGINE MOUNTING SYSTEM AND METHOD | 01-02-2014 |
20140000732 | VALVE ASSEMBLY WITH VALVE POSITION INDICATOR | 01-02-2014 |
20140000272 | METHOD AND SYSTEM FOR OPERATING A TURBINE ENGINE | 01-02-2014 |
20130340438 | METHOD OF REDUCING COMBUSTION INDUCED OSCILLATIONS IN A TURBINE ENGINE - Systems and methods for operating a turbine engine having a plurality of fuel injectors arranged circumferentially in a combustor, with each fuel injector having a main fuel supply and a pilot fuel supply, includes supplying fuel to the plurality of fuel injectors through the main fuel supply to create a circumferential thermal gradient in the combustor. | 12-26-2013 |
20130340436 | GAS FUEL TURBINE ENGINE FOR REDUCED OSCILLATIONS - A gas fuel turbine engine may include a gaseous pilot fuel supply, a first main fuel supply, and a second main fuel supply. The first main fuel supply may provide gaseous fuel to a first plurality of fuel injectors, and the second main fuel supply may provide gaseous fuel to a second plurality of fuel injectors. The turbine engine may also include a flow restriction provided in the first main fuel supply. The second main fuel supply may be free of the flow restriction. | 12-26-2013 |
20130326891 | SHAFT ALIGNMENT TOOLS AND METHODS - The present disclosure is directed to a shaft alignment tool including a base, a rotational body mounted on the base for relative rotation with respect to the base, and an alignment meter coupled to the rotational body. | 12-12-2013 |
20130323058 | TURBINE DAMPER - A damper for a turbine rotor assembly of a gas turbine engine is disclosed. The damper includes a width dimension, a height dimension, and a length dimension, and a forward plate and an aft plate. The aft plate is larger than the forward plate along the width and height dimension and includes an upper portion extending in the height dimension, the upper portion having a non-symmetric configuration. The damper further includes a longitudinal structure extending in the length dimension and connecting the forward plate and the aft plate. | 12-05-2013 |
20130323031 | TURBINE DAMPER - A damper for a turbine rotor assembly of a gas turbine engine is disclosed. The damper includes a width dimension, a height dimension, and a length dimension and a forward plate. The damper further includes an aft plate that is larger than the forward plate along the width and height dimension and having a lower portion including two legs extending in the height dimension. The damper also includes a longitudinal structure extending in the length dimension and connecting the forward plate and the aft plate. | 12-05-2013 |
20130319008 | TURBINE BLADE SUPPORT - A turbine blade is disclosed. The turbine blade includes a platform, an airfoil extending from one side of the platform, a root extending radially from another side of the platform, and a pocket located beneath the platform. The pocket is defined by a plurality of walls, and a pad is disposed in a corner of the pocket. The pad includes three pad corners and three sides connecting the three pad corners, wherein each side extends along a different one of the plurality of walls. | 12-05-2013 |
20130318982 | TURBINE COOLING APPARATUS - The present disclosure describes a turbine blade for a turbine section of a gas turbine engine. The turbine blade includes an airfoil, a platform extending from one side of the airfoil, a root extending from the platform, and at least one purging fin. The at least one purging fin is connected to the root and an underside of the platform, and the at least one purging fin extends along a wall of the root. | 12-05-2013 |
20130312861 | SELF-SEALING TUBE FOR A GAS TURBINE SECONDARY AIR SYSTEM - A self-sealing and self-centering tube made of metal, having a tube axis, and configured to form part of a secondary system in a gas turbine engine is disclosed herein. The self-sealing and self-centering tube includes a tube having a tube wall, an inward end, an outward end, a first seal section located towards the inward end, a second seal section towards the outward end, and an extension section located between the second seal section and the outward end. | 11-28-2013 |
20130312421 | FUEL CONTROL SYSTEM FOR A GAS TURBINE ENGINE - A fuel valve for a gas turbine engine includes a passageway configured to direct a fuel to the engine and a flow restriction positioned in the passageway. The fuel valve may also include a first pressure sensor coupled to the passageway upstream of the restriction through an upstream port, and a second pressure sensor coupled to the passageway downstream of the restriction through a downstream port. The fuel valve may further include a third pressure sensor coupled to the upstream port through a first branch port, and a fourth pressure sensor coupled to the downstream port through a second branch port. | 11-28-2013 |
20130312260 | METHOD AND DEVICE FOR MODIFYING A SECONDARY AIR SYSTEM IN A GAS TURBINE ENGINE - A method and device for modifying a gas turbine engine is disclosed herein. The method for modifying a gas turbine engine includes accessing a first outward end of a first tube installed in the gas turbine engine, the first tube having a tube axis. Then attaching an extraction tool to the first outward end of the first tube, and applying an axial force to the first tube using the extraction tool, the axial force relative to the tube axis, thus breaking a first interference seal between a first interface surface on a first inward end of the first tube and a receiving member of the gas turbine engine. The method continues with removing the first tube from the gas turbine engine. | 11-28-2013 |
20130309085 | COMPRESSOR CASE OVERHAUL - A longitudinally-split compressor case of a gas turbine engine is overhauled to inhibit leakage between case segments that have been distorted. Grooves are machined in mating surfaces of the case segments. Seal wires are located at the grooves. | 11-21-2013 |
20130305508 | SYSTEM AND METHOD FOR MODIFYING A GAS TURBINE ENGINE IN THE FIELD - A system and method for modifying a gas turbine engine in the field to drill a series of cooling holes in a turbine rotor disk made of a superalloy. A portable field repair system includes a stand configured to receive, support, and position a turbine rotor disk, a drill having a self-feeding spindle and configured to automatically drill a predetermined depth through a superalloy and to automatically stop upon completion, a drill guide configured to coordinate the drill with a plurality of radial axes associated with a precise hole pattern to be cut and a drill mount configured to mechanically couple the drill to the drill guide and to position the drill during the modification of the gas turbine engine turbine rotor disk. | 11-21-2013 |
20130298368 | METHODS FOR MANUFACTURING, MODIFYING, AND RETROFITTING A GAS TURBINE INJECTOR - A method for modifying a gas turbine injector is disclosed herein. The method for modifying a gas turbine injector includes removing a first tubular member from the gas turbine injector, replacing the first tubular member with a second tubular member, the second tubular member having a center axis and including a circumferential lip extending radially from the center axis, aiming a laser beam at the circumferential lip so that the laser beam forms an acute angle with the center axis, and, laser welding the second tubular member to the gas turbine injector at the acute angle, the laser welding forming a resultant weld between the second tubular member and the gas turbine injector, and such that at least a portion of the circumferential lip is consumed to form at least a portion of the resultant weld. | 11-14-2013 |
20130283809 | FUEL INJECTOR WITH PURGED INSULATING AIR CAVITY - A fuel injector includes a flow path for fuel air mixture to a combustor extending longitudinally through the fuel injector. The fuel injector may also include a liquid fuel gallery at least partially encircling the flow path. The gallery may include a plurality of fuel spokes configured to deliver liquid fuel from the gallery to the flow path. The fuel injector may also include an annular outer housing circumferentially positioned about the gallery to form an insulating air cavity at least partially around the gallery. The outer housing may include at least one purge hole to provide communication between the insulating air cavity and outside the outer housing of the injector. | 10-31-2013 |
20130259679 | DRY GAS SEAL ASSEMBLY - A seal assembly forms a barrier between a compressor's interior and exterior regions. The seals assembly includes a primary seal stage and a secondary seal stage. The primary seal stage is formed of materials chosen to effectively block flow of gas through the seal assembly. The secondary seal stage is formed of materials chosen to survive a failure of the primary seal stage. | 10-03-2013 |
20130256432 | AIR BLOCKER RING ASSEMBLY WITH LEADING EDGE CONFIGURATION - An air blocker ring assembly including a proximal end and a distal end, a blocker ring, and a blocker ring support cooperating with the blocker ring to form a circumferentially extending split line at an interface between the blocker ring and the blocker ring support. The proximal end of the proximal ring assembly has a circumferential leading edge, and the circumferentially extending split line is located at least one of radially inside or radially outside the leading edge. | 10-03-2013 |
20130256431 | AIR BLOCKER RING ASSEMBLY WITH BLOCKER RING PROTRUSIONS - An air blocker ring assembly includes a proximal end and a distal end, a blocker ring including a protrusion, and a blocker ring support having a recess. The protrusion of the blocker ring is received in the recess. | 10-03-2013 |
20130256386 | HIGH TEMPERATURE BRAZING FIXTURE AND METHOD OF MANUFACTURE - A high temperature brazing fixture and method of manufacture for a gas turbine component made of a superalloy is disclosed herein. The high temperature brazing fixture includes a first and second frame member, a support member, and positioning member, all of which are made from the superalloy and fastened together using tab and tab lock couplings. The support member is configured to interface with and support the gas turbine engine component, and the positioning member is configured to interface with and position at least a first location of or hold a first dimension of the gas turbine component. | 10-03-2013 |
20130255263 | AIR BLOCKER RING ASSEMBLY WITH RADIAL RETENTION - An air blocker ring assembly includes a proximal end and a distal end, a blocker ring, and a blocker ring support. The blocker ring support includes at least one flange radially overlapping a portion of the blocker. | 10-03-2013 |
20130239577 | HYBRID GAS TURBINE ENGINE-ELECTRIC MOTOR/GENERATOR DRIVE SYSTEM - A method of operating a drive system for a load is disclosed. The drive system may have an electric motor/generator and a gas turbine engine. The engine may have a combustor, and main and pilot flow paths via which fuel is supplied to the combustor. The engine may be operable in low and standard emissions modes. A proportion of the fuel that is supplied to the combustor via the pilot flow path may be greater in the standard emissions mode than in the low emissions mode. The method may include determining an engine power requirement of the load, and whether the engine power requirement of the load is sufficiently large to operate the engine in the low emissions mode. Additionally, the method may include operating the electric motor/generator if the engine power requirement of the load is not sufficiently large to operate the engine in the low emissions mode. | 09-19-2013 |
20130232987 | GAS TURBINE FUEL INJECTOR WITH INSULATING AIR SHROUD - A fuel injector for a gas turbine engine is disclosed. The fuel injector includes an injector housing extending from a first end to a second end along a longitudinal axis. The second end of the housing is fluidly coupled to a combustor of the turbine engine and the housing includes a liquid fuel gallery annularly disposed about the longitudinal axis. The fuel injector also includes a stem extending longitudinally from the first end of the housing to a third end. The stem includes a liquid tube configured to deliver liquid fuel to the fuel injector. The fuel injector also includes an annular shell extending along the longitudinal axis from the first end to the third end and circumferentially disposed about the stem. The fuel injector further includes an insulating air shroud formed inside the shell. The air shroud includes a layer of air between the shell and the stem. | 09-12-2013 |
20130227951 | LASER CLAD FUEL INJECTOR PREMIX BARREL - A fuel injector for a gas turbine engine may include a center body disposed about a longitudinal axis, and a premix barrel positioned radially outwardly from the center body to define an annular passageway between the center body and the premix barrel. The annular passageway may extend from an upstream end that is configured to be fluidly coupled to a compressor to a downstream end that is configured to be fluidly coupled to a combustor. The premix barrel may include a first portion at the upstream end and a second portion at the downstream end. The first portion may include a stainless steel material, and the second portion may include a nickel based superalloy material. The second portion may be coupled to the first portion by a laser clad coupling. | 09-05-2013 |
20130224036 | TURBINE ENGINE ROTOR BLADE GROOVE - A rotor blade for a gas turbine engine has an airfoil, a base integrally joined to the airfoil, and a root integrally joined to the base and mountable in a slot in a rotor hub of the gas turbine engine. The root has a dovetail including at least one contact face that, when mounted, contacts a surface of the slot to retain the rotor blade in the hub. The root includes a neck between the base and the dovetail, and a groove in the neck for redirecting stress in the rotor blade. In certain embodiments, the groove is at a distance from the at least one contact face, has a length less than a length of the dovetail, and/or has an initial non-zero depth at the side of a trailing edge of the airfoil and tapers to a zero depth in the direction of the leading edge of the airfoil. | 08-29-2013 |
20130224019 | TURBINE COOLING SYSTEM AND METHOD - A turbine blade of a gas turbine engine is disclosed. The blade may comprise a first cooling passage and a second cooling passage, where the second cooling passage may be located adjacent a leading edge of the blade. The blade may further comprise at least one slot formed in a partition disposed between the first and second cooling passages, and at least one turbulator disposed within the second passage and downstream the at least one slot. | 08-29-2013 |
20130220380 | HOT AIR INJECTOR CLEANING SYSTEM AND PROCESS - A system and process for cleaning a flow passage of a dirty device, such as a fuel injector, are provided. The dirty device has one or more flow passages undesirably clogged with deposit layers of carbon, sulfur, and other contaminants. The device is placed within a thermal chamber heats the device to a first temperature. A fluid supply provides pressurized fluid having an oxidizer, and a heat exchanger heats the pressurized fluid to a second temperature. A conduit is coupled between the heat exchanger the flow passage of the device. The device is heated at the first temperature by the thermal chamber and heated fluid at the second temperature is supplied to the flow passage of the device. The thermal chamber can provide heat to the heat exchanger and the device simultaneously for a period of time. | 08-29-2013 |
20130214492 | GAS TURBINE ENGINE LUBRICATION FLUID BARRIER - A system for forming a barrier between a lubrication oil region and an air region of a gas turbine engine comprising a lubrication oil return path, a centrifugal oil slinger on a rotating member fixed to a spool of the gas turbine engine, a spiral groove configured to directs lubrication oil toward an oil return path, a labyrinth seal, and a cavity configured to form a non-contacting seal with the spiral groove and the labyrinth seal. | 08-22-2013 |
20130213152 | Analysis of Localized Waste Material - A testing method for a component is provided. The method identifies a flaw region of the component. The flaw region is prone to defects. The method then isolates a waste material associated with the identified flaw region. The method analyzes the isolated waste material for an undesirable microstructure associated with defects. Subsequently, the method determines rejection and acceptance of the component based, at least in part, on the analysis. | 08-22-2013 |
20130213045 | Coated Porous Metallic Mat - A porous metallic mat is provided. The porous metallic mat includes a plurality of fibers and a protective coating. The plurality of fibers is sintered into a mat configuration. The protective coating is provided on the porous metallic mat. The protective coating includes a diffusion aluminide configured to provide oxidation resistance to the porous metallic mat. | 08-22-2013 |
20130168472 | METHOD AND APPARATUS FOR SWAGED LIQUID INJECTOR SPOKE - A liquid fuel injection spoke for a gas turbine engine. The liquid fuel injection spoke may include an inlet end and an outlet end. The liquid fuel injection spoke may further include a head located at the inlet end and a stem extending along a longitudinal axis from the head to the outlet end. The stem may define a fluid passageway therein. The head may include a cavity with an inner wall. The inner wall may include an annular protrusion. | 07-04-2013 |
20130081401 | IMPINGEMENT COOLING OF COMBUSTOR LINERS - A gas turbine engine may include an impingement cooled double-walled liner, having an inner liner and an outer liner, disposed around a combustion space of the turbine engine. The double-walled liner may extend from an upstream end to a downstream end. The gas turbine engine may also include a plurality of nozzles extending radially inwards through the outer liner to direct cooling air towards the inner liner. Each nozzle of the plurality of nozzles may extend radially inwards from a first distal end to a second proximal end. The plurality of nozzles may be arranged such that a radial gap between the second end of a nozzle and the outer liner decreases from the upstream end to the downstream end. The at least one nozzle of the plurality of nozzles may include multiple air holes at the second end. | 04-04-2013 |
20130004337 | SYSTEM AND METHOD FOR DRIVING A PUMP - A system for driving a pump includes a gas turbine engine having an output shaft, and a torque converter including an input shaft coupled to the output shaft of the gas turbine engine and an output shaft configured to be coupled to an input shaft of a pump. The system further includes a controller coupled to the torque converter, wherein the controller is configured to receive a signal indicative of a pressure at at least one of a pump inlet and a pump outlet, and control a speed of the output shaft of the torque converter based on the signal indicative of pressure. | 01-03-2013 |
20120144188 | METHOD FOR CONNECTING A FIRST COMPUTER NETWORK TO AT LEAST A SECOND EXTENDED COMPUTER NETWORK - Method for connecting a first computer network and at least a second extended computer network wherein the at least second extended computer network is not connected to the Internet and does not have a routing path to the first computer network, the method comprising: installing a concentration router within an intermediate network and associating the concentration router to a public IP address; interconnecting the intermediate network to the at least second extended computer network through a CPE router, and interconnecting the intermediate network to the first computer network via the Internet passing through the concentration router; implementing an IP tunnel between the at least second extended computer network and the first computer network across the direct intermediate network and the Internet, wherein the IP tunnel is implemented as a first external and encrypted IP tunnel, across the Internet, and a second internal non-encrypted IP tunnel across the intermediate network. | 06-07-2012 |
20100326080 | Acoustically Tuned Combustion for a Gas Turbine Engine - A fuel nozzle for a turbine engine has a central body member with a pilot, a surrounding barrel housing, a mixing duct and an air inlet duct. The fuel nozzle additionally has a main fuel injection device located between the air inlet duct and the mixing duct. The main fuel injection device is configured to introduce a flow of fuel into the barrel member to create a fuel/air mixture which is then premixed with a swirler. The fuel/air mixture then further mixes in the mixing duct and exits the nozzle into a combustor for combustion. The geometry of the fuel nozzle ensures that pressure waves from the combustor do not create a time varying fuel to air equivalence ratio in the flow through the nozzle that achieves a resonance with the pressure waves. | 12-30-2010 |
20100287947 | Acoustically Tuned Combustion for a Gas Turbine Engine - A fuel nozzle for a turbine engine has a central body member with a pilot, a surrounding barrel housing, a mixing duct and an air inlet duct. The fuel nozzle additionally has a main fuel injection device located between the air inlet duct and the mixing duct. The main fuel injection device is configured to introduce a flow of fuel into the barrel member to create a fuel/air mixture which is then premixed with a swirler. The fuel/air mixture then further mixes in the mixing duct and exits the nozzle into a combustor for combustion. The geometry of the fuel nozzle ensures that pressure waves from the combustor do not create a time varying fuel to air equivalence ratio in the flow through the nozzle that achieves a resonance with the pressure waves. | 11-18-2010 |