Entries |
Document | Title | Date |
20080236169 | COMBUSTOR FLOATING COLLAR WITH LOUVER - A gas turbine combuster ia provided with a dome heat shield having a fuel nozzle opening, the opening receiving a floating collar assembly for permitting relative movement between nozzle and heat shield. The floating collar is provided with a louver to provide film cooling to the face of the combustor heat shield and, thus, improve cooling thereof. | 10-02-2008 |
20090158747 | METHOD FOR THE CONTROLLED PURGING OF THE FUEL FEEDING SYSTEM IN THE COMBUSTOR OF A GAS TURBINE - A method is described for the controlled purging of the fuel feeding system in the combustor of a gas turbine comprising at least one compressor, capable of compressing the air introduced into it through an inlet duct, at least one combustor, in which said compressed air is mixed and combusted with a gaseous fuel coming from a feeding duct, and at least one turbine, capable of transforming the energy of the combusted gas coming from said combustion chamber into work energy which can be exploited for activating one or more operating machines. The combustor is equipped with one or more burners, each equipped with at least one pilot injector and one or more main injectors for the adduction of the gaseous fuel inside the burner. The method comprises purging at least part of the main injectors and relative manifolds with a stream of gaseous fuel when the turbine is in diffusive flame functioning mode. | 06-25-2009 |
20100024431 | METHOD OF DETECTING A PARTIAL FLAME FAILURE IN A GAS TURBINE ENGINE AND A GAS TURBINE ENGINE - A method of detecting a partial flame failure in a gas turbine is provided. The method includes a gas duct to guide a propulsion gas and several combustors, each combustor leads into the gas duct and includes a burner. The method includes measuring a first temperature over time at each of at least two probing points located downstream from the combustors in the gas duct, measuring a second temperature over time in each of at least two of the burners, and detecting a partial flame failure from the first temperature measurements and the second temperature measurements, wherein the detecting of a partial flame failure includes determining a first detection parameter, the first detection parameter is determined from a rate of change of a variation between the first temperature measurements at different probing points. A gas turbine including temperature sensors to detect a partial flame failure is also provided. | 02-04-2010 |
20100257867 | MONITORING OF A HIGH-PRESSURE PUMP IN A TURBINE ENGINE FUEL SUPPLY CIRCUIT - A device and method for monitoring a high-pressure pump in a turbomachine fuel supply circuit by detecting opening of a pressurizing and shut-off valve mounted on an outlet side of a fuel flow regulating valve, by measuring rotational speed of the turbomachine corresponding to the opening of the pressurizing and cut-off valve, and by monitoring change in a value of the rotational speed to propose replacement of the high-pressure pump when the measure value rotational speed reaches a predetermined threshold. | 10-14-2010 |
20100319358 | Nosecone ice protection system for a gas turbine engine - A system includes a first anti-icing electrothermal heater located at tip of a gas turbine engine nosecone, and a plurality of anti-icing electrothermal heater strips extending rearward from the first anti-icing electrothermal heater along the nosecone. | 12-23-2010 |
20110041512 | OVERSPEED PROTECTION APPARATUS FOR GAS TURBINE ENGINE - In an overspeed protection apparatus for a gas turbine engine having a turbine rotated by combustion gas injected from a combustion chamber to drive a compressor, a fuel shutoff valve to shut off fuel to be supplied to the engine and a controller controlling operation of the fuel shutoff valve based on a turbine rotational speed to protect the turbine from overspeed, an outlet pressure of the compressor is detected and compared with a threshold value when a shutoff command is outputted, and the fuel shutoff valve is determined to be failed when the detected pressure is not less than the threshold value, thereby enabling to promptly detect the fuel shutoff valve failure without additional installing sensor, thereby enhancing the reliability | 02-24-2011 |
20110079015 | APPARATUS AND METHOD OF OPERATING A GAS TURBINE ENGINE - A gas turbine engine and an apparatus for operating the gas turbine engine includes at least one microphone to detect the sound of impacts of particles, recorder to record the sound of the impacts, an analyser to analyse the sound of the impacts of the particles, and a store of sounds of impacts, the stored sounds of impacts correspond to unfavourable weather conditions. A comparator compares the sound of the impacts of particles with one or more sounds of impacts stored in the store | 04-07-2011 |
20110146294 | AIRPLANE ENGINE DEFLECTOR SYSTEMS - A protective deflector for airplane engines system is disclosed herein comprising a turbine-covering screen assembly which may be installed to an airplane engine turbine housing by a securable fastening device. The turbine-covering screen assembly comprises a protruded bell-shaped extrusion member having a plurality of apertures which may serve to prevent birds, objects and other debris from penetrating a turbine housing air-intake opening thereby protecting an airplane engine from interference during flight. The turbine-covering screen assembly does not appreciably affect the performance of the turbine engine it serves to protect. | 06-23-2011 |
20110232297 | METHOD AND SYSTEM FOR TESTING AN OVERSPEED PROTECTION SYSTEM OF A POWERPLANT MACHINE - Embodiments of the present invention have the technical effect of automatically testing an overspeed protection system of a powerplant machine comprising at least one shaft. An embodiment of the present invention may automatically test the overspeed protection system while the powerplant machine is decelerating from full-speed-no-load (FSNL). Another embodiment of the present invention may automatically test the overspeed protection system of the powerplant machine while the powerplant machine is accelerating to FSNL. | 09-29-2011 |
20120085101 | METHOD OF TESTING A SYSTEM FOR PROTECTING A TURBOMACHINE AGAINST OVERSPEED WHILE STARTING - In a testing overspeed protection system: a) on receiving an order to start a turbomachine, an electronic regulation system (ERS) of the turbomachine sends an order to a control circuit of a fuel cutoff member to close the fuel cutoff member or to keep it in the closed position; b) the closed state of the FCM is verified on the basis of information transmitted to the ERS and representative of the position of the FCM; c) if the result of the verification in b) is positive, the ERS sends an order to the FCM control circuit to authorize opening of the FCM and enable the starting procedure to continue; and d) if the result of the verification in b) is negative, the ERS issues fault information concerning the overspeed protection system. | 04-12-2012 |
20120125009 | AIRCRAFT SAFETY DEVICE SYSTEMS - An aircraft system comprising a deflector assembly including, a base having mounting apertures; an inner ring concentrically positioned within an outer ring, the inner ring and the outer ring have an annulus defined therebetween via a base plate, a plurality of rods attached within the annulus and culminating at an apex creating a conical profile; and a forward-mounted cone-shaped deflecting member. The base plate comprises a through hole allowing airflow through the deflector assembly to supply an airplane engine. The aircraft safety device system further comprises at least one locking latch for removably securing the deflector assembly to a housing of the airplane engine. The aircraft safety device is mountable inside a lip of the housing of the airplane engine. Further, the aircraft safety device provides protection for airplane engines from air born animate and inanimate objects. | 05-24-2012 |
20120137699 | Method and device for purging a gas turbine liquid fuel injection system - Device for purging a feed device ( | 06-07-2012 |
20120174595 | ARRANGEMENT FOR MAINTAINING FLOW TO AN AIR INLET OF AN AUXILIARY POWER UNIT ASSEMBLY - An example auxiliary power unit air inlet assembly includes a noise attenuating component disposed within a conduit. The conduit is configured to communicate a first flow of fluid to an auxiliary power unit. A second flow of fluid is communicated to the noise attenuating component. The second flow of fluid limits formation of ice in the conduit. The first flow of fluid is different than the second flow of fluid. | 07-12-2012 |
20120204572 | METHOD AND DEVICE FOR DETERMINING THE CAPACITY OF AN AIRCRAFT PUMP TO DELIVER A PREDETERMINED FUEL OUTPUT - The invention proposes a method for determining the capacity of an aircraft pump to deliver a predetermined fuel flow rate, | 08-16-2012 |
20120216548 | SYSTEMS AND METHODS INVOLVING MULTIPLE TORQUE PATHS FOR GAS TURBINE ENGINES - Systems and methods involving multiple torque paths of gas turbine engines are provided. In this regard, a representative method for reducing overspeed potential of a turbine of a gas turbine engine includes: providing a first load to the turbine via a first torque path; providing a second load to the turbine via a second torque path; and operating the turbine such that: mechanical failure of a component defining at least a portion of the first torque path does not inhibit the second load from being applied to the turbine via the second torque path; and mechanical failure of a component defining the second torque path does not inhibit the first load from being applied to the turbine via the first torque path. | 08-30-2012 |
20120240593 | FUEL SYSTEM FOR GAS TURBINE ENGINE - A method and apparatus for heating fuel in an aircraft gas turbine engine, for example to provide fuel anti-icing to the fuel, comprises directing a fuel flow through a heat exchanger associated with a generator power conditioning unit as a sole means for providing anti-icing heating to fuel supplied for engine combustion. The method and apparatus permits the heat exchanger to heat the fuel sufficiently so that other dedicated heating means may be unnecessary. | 09-27-2012 |
20120260667 | Power Plant - A power plant is provided and includes a gas turbine engine to generate power, a heat recovery steam generator (HRSG) to produce steam from high energy fluids produced from the generation of power in the gas turbine engine, a steam turbine engine to generate additional power from the steam produced in the HRSG and a thermal load reduction system to reduce thermal loading of components of the HRSG and/or the steam turbine engine during at least startup and/or part load operations, which includes an eductor by which a mixture of compressor discharge air and entrained ambient air is injectable into the HRSG and/or an attemperator to cool superheated steam to be transmitted to the steam turbine engine and a detector disposed within the HRSG to facilitate identification of hot spots therein. | 10-18-2012 |
20120324906 | HEAT PROTECTION SYSTEM - A heat and/or fire protection assembly for a component, the assembly comprising: a plurality of protrusions distributed about a surface of the component, the protrusions protruding with respect to the surface of the component; the protrusions comprising a barrier material, the barrier material being arranged and configured to form a first protective layer under the action of heat, the first protective layer being arranged to protect the component from the heat. | 12-27-2012 |
20130000318 | ECOLOGY SYSTEM FOR DRAINING THE MANIFOLD OF A GAS TURBINE ENGINE - A fuel system including a fuel pump metering unit (FPMU) for delivering fuel to an engine manifold with an ecology valve for draining and storing fuel from the engine manifold. The ecology valve includes a housing having a piston dividing the housing into a first side in fluid communication with an output of the FPMU and a second side in fluid communication with the engine manifold. An assembly connected between the FPMU and engine manifold selectively creates a pressure differential across the first and second side of the housing when the FPMU delivers fuel to the engine manifold. In a run position, the piston moves to decrease a volume within the housing interior as a result of the pressure differential. In a drain position, the piston moves to increase the housing volume within the interior and thereby pull and store fuel from the engine manifold. | 01-03-2013 |
20130008174 | METHOD AND CONTROLLER FOR DETECTING ICE - An example method of aircraft engine control includes detecting a difference between a temperature detected by a first temperature sensor and a temperature detected by a second temperature sensor. Anti-icing activity is initiated in response to the difference. | 01-10-2013 |
20130019608 | METHOD OF INHIBITING ICE ACCRETION WITHIN A TURBINE ENGINE AND CONTROL SYSTEM THEREFOR - A method of inhibiting ice accretion within a turbine engine | 01-24-2013 |
20130055723 | Apparatus and Method for Separating Ice from Fuel in a Gas Turbine Engine - According to one aspect of the invention, an ice separating apparatus for a gas turbine engine includes a can having a first end and a tangential inlet proximate the first end of the can to receive a fluid flow within the can, wherein the fluid flow includes fuel and ice. The apparatus also includes a first conduit within the can to receive a separated fuel flow proximate a second end of the can, wherein the fluid flow separates ice from fuel to form the separated fuel flow. | 03-07-2013 |
20130061599 | FUEL MANIFOLD COOLING FLOW RECIRCULATION - Cooling flow recirculation in fuel manifolds, such as fuel manifolds associated with gas turbine engines is disclosed. An example system for jet pump driven recirculation of manifold cooling flow according to at least some aspects of the present disclosure may include a flow split valve having a spool valve disposed therein, the flow split valve having a pilot manifold and a main manifold attached thereto; a jet pump fluidically coupled to the pilot manifold, the jet pump being arranged to drive recirculation of a cooling flow through the main manifold via a cooling flow circuit in a pilot only mode of operation; and/or a fuel nozzle in fluid communication with the pilot manifold and the main manifold. | 03-14-2013 |
20130098057 | CONTROLLABLE SPEED WINDMILL OPERATION OF A GAS TURBINE ENGINE THROUGH LOW SPOOL POWER EXTRACTION - A gas turbine engine that includes at least one component geared to a spool to control a speed of the low spool during a “windmilling” condition. | 04-25-2013 |
20130133333 | SHAFT BREAK DETECTION - The present invention provides a method of detecting shaft break in a shaft system comprising a shaft coupled between two masses. The method comprises a number of steps. Firstly, to define a time-dependent rotational speed equation for the shaft in terms of system inertia for an engine transient event. Then to discretize the rotational speed equation in terms of a discrete time constant in the discrete domain. Then to recursively define the discretized equation to give a recursive equation and to solve the recursive equation to determine the discrete time constant. Then to define a threshold as a function of engine power and then to set a shaft break signal to TRUE if the discrete time constant is greater than the threshold. A shaft break detection system is also provided by the present invention. | 05-30-2013 |
20130139520 | METHOD FOR MONITORING A CONTROL DEVICE OF A FUEL METERING VALVE OF A TURBOJET ENGINE - A method for monitoring a control device of a fuel metering valve of an aircraft turbojet engine, the control device supplying a control current) to a servo valve in order to modify the position of the fuel metering valve, the method comprising:
| 06-06-2013 |
20130152599 | HYDROCARBON FILM PROTECTED REFRACTORY CARBIDE COMPONENTS AND USE - A turbine power generation system with enhanced stabilization of refractory carbides provided by hydrocarbon from high carbon activity gases is disclosed. The disclosure also includes a method of using high carbon activity gases to stabilize hot gas path components. | 06-20-2013 |
20130152600 | SHAFT BREAK DETECTION - A method to detect shaft break includes monitoring first and second parameters and defining a two-dimensional parameter space that is a function of the first and second parameters, the two-dimensional parameter space includes integration regions. The method also includes defining an integration function for each integration region. For measured values of the first and second parameters, the method determines the applicable integration region and applies the integration function to the first parameter to give an integration result; and then sets a shaft break signal to TRUE when the integration result exceeds a predetermined threshold. The present invention also provides a shaft break detection system. | 06-20-2013 |
20130160457 | SYSTEM AND METHOD FOR IMPROVED COMBUSTOR TEMPERATURE UNIFORMITY - A combustor and a method for reducing a temperature gradient of a combustor component are provided. The combustor includes a coating applied to at least a portion thereof with the coating serving to alter the emissivity of the at least a portion to which it is applied. The method includes applying a coating on at least one of a combustor liner and a flow sleeve, wherein the coating alters the emissivity exhibited where applied. | 06-27-2013 |
20130180261 | COMBUSTOR AND METHOD FOR REDUCING THERMAL STRESSES IN A COMBUSTOR - A combustor includes first and second annular casings with a joint between the first and second annular casings. A flow sleeve surrounds a combustion chamber to define an annular passage, and an annular shield inside the first annular casing extends downstream from the joint and prevents a working fluid flowing through the annular passage from contacting at least a portion of the first annular casing. A method for reducing thermal stresses in a combustor includes flowing a working fluid from a compressor through an annular passage between a combustion chamber and a flow sleeve inside the combustor, shielding the working fluid flowing through the annular passage from contact with at least a portion of a joint between first and second annular casings, and shielding the working fluid flowing through the annular passage from contact with at least a portion of the first annular casing downstream from the joint. | 07-18-2013 |
20130192247 | GAS TURBINE ENGINE VARIABLE AREA FAN NOZZLE WITH ICE MANAGEMENT - A method of managing a gas turbine engine variable area fan nozzle includes the steps of evaluating an icing condition to determine the likelihood of ice presence. A variable area fan nozzle position is altered if ice is likely present or actually present. The gas turbine engine includes a fan nacelle including a flap configured to be moveable between first and second positions. An actuator is operatively coupled to the flap. A controller is configured to evaluate an icing condition to determine the likelihood of ice presence. The controller is configured to alter a variable area fan nozzle position schedule if ice is likely present by providing a command to the actuator to adjust the flap from the first position to the second position. | 08-01-2013 |
20130192248 | GAS TURBINE ENGINE BUFFER SYSTEM - A gas turbine engine includes a buffer system. The buffer system can include a first bleed air supply and a conditioning device that conditions the first bleed air supply to render the buffer supply air at an acceptable temperature to anti-ice the hardware of said fan section. | 08-01-2013 |
20130199202 | SYSTEM AND METHOD FOR GAS TURBINE INLET AIR HEATING - In one embodiment of the present disclosure, a gas turbine system for part load efficiency improvement and anti-icing within the inlet and at the compressor inlet is described. The system includes a gas turbine having a compressor which receives inlet-air. A direct-contact heat exchanger heats the inlet-air before the inlet-air flows through the inlet and to the compressor. Heating the inlet-air reduces an output of the gas turbine and extends the turndown range, and avoids ice-forming conditions within the inlet and at the compressor inlet bellmouth. The direct-contact heat exchanger may also be configured to act as an evaporative cooler, air chiller, or use liquid dessicant. | 08-08-2013 |
20130199203 | Linear Detonation Wave Diverter - The presently disclosed linear detonation wave diverter provides a structure and method for quickly and controllably venting a detonation event out of the diverter without igniting working fluid upstream of a microporous barrier within the linear detonation wave diverter. Further, the detonation wave is linearly vented out of the diverter upon the failure of a burst member, which provides a low resistance path for detonation waves to exit the detonation wave diverter. | 08-08-2013 |
20130199204 | METHOD AND A DEVICE FOR PERFORMING A CHECK OF THE HEALTH OF A TURBINE ENGINE OF AN AIRCRAFT PROVIDED WITH AT LEAST ONE TURBINE ENGINE - A method of automatically performing an engine health check for checking the health of at least one turbine engine of an aircraft. During flight, the stability of at least one monitoring parameter is verified by acquiring a measurement signal, by performing first filtering of each signal by a high-pass filter over a long first duration (TPS | 08-08-2013 |
20130219912 | COMBUSTOR AND METHOD FOR PURGING A COMBUSTOR - A combustor includes an end cap. The end cap includes a first surface and a second surface downstream from the first surface, a shroud that circumferentially surrounds at least a portion of the first and second surfaces, a plate that extends radially within the shroud, a plurality of tubes that extend through the plate and the first and second surfaces, and a first purge port that extends through one or more of the plurality of tubes, wherein the purge port is axially aligned with the plate. | 08-29-2013 |
20130219913 | GEARED TURBOFAN GAS TURBINE ENGINE WITH RELIABILITY CHECK ON GEAR CONNECTION - A gas turbine engine includes a fan and a compressor. A combustor drives a turbine, including a first turbine with a shaft to drive the compressor. A fan drive turbine drives the fan through a speed reduction. A sensor senses a speed of rotation of the fan and communicates sensed speed information to a control. The control develops an expected speed for the fan. A problem is identified should the sensed speed be less than the expected speed by more than a predetermined amount. A method is also described. | 08-29-2013 |
20130232989 | GAS TURBINE ENGINE FUEL HEATING SYSTEM - A fuel heating system for a gas turbine engine comprises a first heat exchanger, a second heat exchanger, a fuel pump and a valve. The first heat exchanger produces a heated air flow. The second heat exchanger receives the heated air flow from the first heat exchanger. The fuel pump provides a fuel flow. The valve is coupled to the fuel pump to intermittently include the second heat exchanger in the fuel flow based on a temperature of the fuel flow. A method of heating fuel in a gas turbine engine comprises providing fuel to a gas turbine engine with a fuel pump to sustain a combustion process, heating a flow of air with exhaust gas from the combustion process, and heating fuel from the fuel pump en route to the gas turbine engine with the flow of air based on a temperature of the fuel. | 09-12-2013 |
20130239581 | Systems and Methods for Preventing Flashback in a Combustor Assembly - Embodiments of the present application include a combustor assembly. The combustor assembly may include a combustion chamber, a first plenum, a second plenum, and one or more elongate air/fuel premixing injection tubes. Each of the elongate air/fuel premixing injection tubes may include a first length at least partially disposed within the first plenum and configured to receive a first fluid from the first plenum. Moreover, each of the elongate air/fuel premixing injection tubes may include a second length disposed downstream of the first length and at least partially disposed within the second plenum. The second length may be formed of a porous wall configured to allow a second fluid from the second plenum to enter the second length and create a boundary layer about the porous wall. | 09-19-2013 |
20130247580 | SYSTEM AND METHOD FOR RECIRCULATING A HOT GAS FLOWING THROUGH A GAS TURBINE - A system for recirculating a hot gas flowing through a gas turbine generally includes a transition piece having a downstream surface, a stationary nozzle having a leading edge surface adjacent to the transition piece downstream surface, a gap defined between the transition piece downstream surface and the stationary nozzle leading edge surface, and a projection having an inner arcuate surface radially separated from an outer surface. The projection generally extends from the stationary nozzle leading edge surface towards the transition piece downstream surface and at least partially decreases the gap. A seal extends across the gap and may be in contact with the transition piece and the stationary nozzle leading edge surface. A recirculation zone may be at least partially defined between the projection inner arcuate surface, the stationary nozzle leading edge surface and the transition piece downstream surface. | 09-26-2013 |
20130247581 | Systems and Methods for Dampening Combustor Dynamics in a Micromixer - Embodiments of the present application can provide systems and methods for dampening combustor dynamics. According to one embodiment, the system may include a micromixer. The system may also include at least one annular resonator disposed within the micromixer adjacent to a cap face plate or an impingement plate of the micromixer. The at least one annular resonator may include a first side including a number of holes forming a cold side hole pattern, a second side including a number of holes forming a hot side hole pattern, and a cavity substantially defined by the first side and the second side. | 09-26-2013 |
20130269364 | Systems and Methods for Detecting Fuel Leaks in Gas Turbine Engines - Embodiments can provide systems and methods for detecting fuel leaks in gas turbine engines. According to one embodiment, there is disclosed a method for detecting a fuel leak in a gas turbine engine. The method may include adjusting a control valve to correspond with a desired fuel flow. The method may also include determining an actual fuel flow based at least in part on an upstream pressure in a fuel manifold and one or more gas turbine engine parameters. The method may also include comparing the desired fuel flow with the actual fuel flow. Moreover, the method may include determining a difference between the desired fuel flow and the actual fuel flow, wherein the difference indicates a fuel leak. | 10-17-2013 |
20130283812 | SYSTEMS AND METHODS FOR RECONDITIONING TURBINE ENGINES IN POWER GENERATION SYSTEMS - A flow control system is provided. The flow control system includes at least one control valve coupled to at least one nozzle of a turbine engine, wherein the control valve is configured to regulate fluid flow in a first direction or a second direction. The first direction is when the fluid is channeled from a compressor to the nozzle and the second direction is when the fluid is channeled from the nozzle to an exhaust section of the turbine engine. A controller is coupled to the control valve and is configured to control the fluid flow in the first direction during operation of the turbine engine and to change the direction of the fluid flow from the first direction to the second direction to facilitate reconditioning of the turbine engine. | 10-31-2013 |
20130291552 | ELECTRICAL CONTROL OF COMBUSTION - A system for electrically controlling combustion includes a combustion chamber, one or more sensors, an actuator, and a controller. The controller detects dynamic instabilities based upon input regarding conditions in the combustion chamber from the sensors. The actuator electrically modulates combustion, and the controller operates the actuator to counteract the dynamic instabilities. | 11-07-2013 |
20130305737 | SYSTEM AND METHOD FOR HEAT RECOVERY IN A GAS TURBINE ENGINE - A system includes an anti-icing heat recovery system, which includes a first heat exchanger, a second heat exchanger, and a variable speed fan. The first heat exchanger is configured to receive a working fluid from an exhaust section of a gas turbine engine and to transfer heat from the working fluid to a cooled intermediate heat transfer medium to generate a heated intermediate heat transfer medium. The second heat exchanger is configured to receive the heated intermediate heat transfer medium from the first heat exchanger and to transfer heat from the heated intermediate heat transfer medium to air entering the gas turbine engine. The variable speed fan is configured to urge the working fluid from the exhaust section of the gas turbine engine through the first heat exchanger. | 11-21-2013 |
20130312423 | METHOD OF DETECTING SHAFT BREAK - A method of detecting shaft break in a gas turbine engine having a shaft system. The shaft system including a shaft that couples a compressor and a turbine. First construct a frequency model of the shaft system. Then determine a notch frequency and a first torsional frequency for the shaft system from the model. Then in real time measure a rotational speed of the shaft; detect the presence or absence of a feature at at least one of the notch frequency and the first torsional frequency in the measured speed; and generate a shaft break signal in response to the absence of at least one of the features. | 11-28-2013 |
20130318993 | UTILIZATION OF FUEL GAS FOR PURGING A DORMANT FUEL GAS CIRCUIT - An approach for utilizing fuel gas to purge a dormant fuel gas circuit is disclosed. In one aspect, there is a fuel gas supply that supplies fuel to fuel gas circuits. Gas control valves, each coupled to one of the fuel gas circuits control the flow of fuel gas thereto from the fuel gas supply. A fuel purge system selectively purges fuel gas circuits from the fuel gas circuits that are dormant with fuel gas from the fuel gas supply. | 12-05-2013 |
20130318994 | ULTRA-VIOLET FLAME DETECTOR WITH HIGH TEMPERATURE REMOTE SENSING ELEMENT - A flame sensor apparatus is provided including a sensor assembly for sensing characteristics of a flame within a combustion chamber. The flame sensor apparatus further includes an electrical assembly that is electrically remote from the sensor assembly. In addition, a cable assembly extends between the sensor assembly and the electrical assembly. The cable assembly can convey the characteristics of the flame from the photodiode to the electrical assembly. The cable assembly is included as part of a sealed array filled with an inert gas. In addition, a method of sensing characteristics of a flame is also provided. | 12-05-2013 |
20130340439 | Systems and Methods for De-Icing a Gas Turbine Engine Inlet Screen and Dehumidifying Inlet Air Filters - A system for de-icing a gas turbine engine is provided. A manifold is coupled to an inlet screen. A first conduit is coupled to a stage of the compressor and a first input of a mixing component. A second conduit is coupled to the exhaust and a second input of the mixing component. The second conduit being adapted to extract exhaust gases without increasing the pressure at the exhaust. A third conduit is coupled to the output of the mixing component and the manifold. A method for de-icing a gas turbine engine inlet screen includes determining a current temperature at the inlet screen, and determining a desired temperature at the inlet screen. If the current temperature at the inlet screen is less than the desired temperature at the inlet screen first flow rate of an air-exhaust mixture necessary to achieve the desired inlet screen temperature is calculated. The method also includes extracting an amount of exhaust gas from a turbine exhaust subsystem without increasing a pressure at the turbine exhaust subsystem, extracting an amount of air from a compressor stage, and mixing the amount of exhaust gas with the amount of air to generate an air-exhaust mixture that is conveyed to the inlet screen. | 12-26-2013 |
20140013765 | METHOD AND ARRANGEMENT FOR GAS TURBINE ENGINE SURGE CONTROL - The invention relates to a surge control method for a gas turbine engine. The method includes providing a gas turbine engine having a compressor, a combustor, downstream of the compressor, with a hot gas path, a turbine downstream of the combustor, with a hot gas path. The method further includes monitoring the gas turbine engine for a potential surge condition, controlling a blow-off flow from the compressor, based on the monitoring for the control purpose of avoiding the surge condition, and directing the blow-off flow to at least one of the hot gas paths so as to bypass at least a portion of the combustor. | 01-16-2014 |
20140041393 | SYSTEMS AND METHODS FOR PROCESSING INLET AIR - An air processing assembly is provided. The assembly includes at least one filter element that includes a filter media having a first end and a second end spaced a predefined distance from the first end. A channel is defined within the filter media, wherein the channel extends from the filter media first end to the filter media second end. The channel defines a flow path for a solid desiccant, wherein air being channeled through the assembly is filtered via the filter media and moisture is substantially removed from the air via the solid desiccant. | 02-13-2014 |
20140075953 | SYSTEM AND METHOD FOR DETECTING AND CONTROLLING FLASHBACK AND FLAME HOLDING WITHIN A COMBUSTOR - A system is provided for detecting and controlling flashback and flame holding in a combustor of a gas turbine. The system includes at least one flame indicator disposed in a combustor and at least one detector disposed downstream from the flame indicator. The flame indicator may be configured to produce light when exposed to a flame and the detector may be configured to detect the light produced by the flame indicator. | 03-20-2014 |
20140075954 | Methods And Systems For Substance Profile Measurements In Gas Turbine Exhaust - Methods and systems for substance profile measurements in gas turbine exhaust. In an embodiment, a concentration of a substance may be determined and associated with a combustor out of a plurality of combustors. An alert may be transmitted in reference to the combustor when the concentration of the substance crosses a threshold level. | 03-20-2014 |
20140083111 | GAS TURBINE ASYMMETRIC FUEL NOZZLE COMBUSTOR - A combustor of a gas turbine engine includes a multiple of fuel nozzles arranged asymmetrically | 03-27-2014 |
20140102113 | EXHAUST HEAT RECOVERY FOR A GAS TURBINE SYSTEM - A system includes a gas turbine and an anti-icing system coupled to the gas turbine. The gas turbine is configured to receive air and fuel and to combust a mixture of the air and the fuel into exhaust gases. The anti-icing system is configured to use heat from the exhaust gases to heat a heat transfer fluid (HTF) and to selectively heat the fuel and the air via the HTF. | 04-17-2014 |
20140109589 | GAS TURBINE ENGINE VARIABLE BLEED VALVE FOR ICE EXTRACTION - A variable bleed valve includes a variable bleed valve door disposed in a bleed inlet in transition duct and rotatable about an axis at or near a forward end of door. Valve is operable to open and close a bleed slot open to a booster bleed flowpath located outwardly of transition duct and having an airflow restrictor. Airflow restrictor may be variable such as a flapper valve. Booster bleed flowpath may pass through a bifurcated bleed duct including an inner passage radially bound by spaced apart inner and middle bleed walls and an outer passage radially bound by middle bleed wall and an outer bleed wall. Airflow restrictor may include an outlet area smaller than an inlet area of inner passage. Door seals against middle bleed wall to open inner passage and against outer bleed wall to open both passages. | 04-24-2014 |
20140196468 | COMBUSTION ARRANGEMENT AND TURBINE COMPRISING A DAMPING FACILITY - A combustion arrangement for a turbine is provided including: a casing; a combustion chamber within the casing, an inner casing volume may be defined as a volume inside the casing but outside the combustion chamber; a partitioning wall partitioning the inner casing volume into first and second volume portions, the partitioning wall may have at least one aperture to allow fluid communication between the first and second volume portions; and a valve may be arranged at the casing to allow an outgoing fluid flow from the inner casing volume to an outside of the casing depending on a valve operating position. The combustion chamber has a combustion entry port for supplying an oxidant into the combustion chamber, where the combustion entry port may be in fluid communication with the first volume portion. The arrangement may be adapted to adjust the valve operating position for damping an oscillation of the arrangement. | 07-17-2014 |
20140216053 | GEARED TURBOFAN GAS TURBINE ENGINE WITH RELIABILITY CHECK ON GEAR CONNECTION - A gas turbine engine includes a fan and a compressor. A combustor drives a turbine, including a first turbine with a shaft to drive the compressor. A fan drive turbine drives the fan through a speed reduction. A sensor senses a speed of rotation of the fan and communicates sensed speed information to a control. The control develops an expected speed for the fan. A problem is identified should the sensed speed be less than the expected speed by more than a predetermined amount. A method is also described. | 08-07-2014 |
20140238041 | COMBUSTOR CAN TEMPERATURE CONTROL SYSTEM - The present application provides a fuel delivery system for a combustor with reduced coherence and/or reduced combustion dynamics. The combustor can assembly may include a first manifold for delivering a first flow of fuel to a first set of fuel injectors and a second manifold for delivering a second flow of fuel to a second set of fuel injectors. The first flow of fuel may have a first temperature and the second flow of fuel may have a second temperature. The first temperature may be higher than the second temperature. | 08-28-2014 |
20140245746 | COMBUSTION ARRANGEMENT AND METHOD OF REDUCING PRESSURE FLUCTUATIONS OF A COMBUSTION ARRANGEMENT - A combustion arrangement includes a combustion section. Also included is an air discharge section downstream of the combustion section. Further included is a transition region disposed between the combustion section and the air discharge section. Yet further included is a transition piece defining the combustion section and the transition region, wherein the transition piece is configured to carry a combusted gas flow from the combustion section to the air discharge section. Also included is a damping device operatively coupled to the transition piece proximate the air discharge section. | 09-04-2014 |
20140260307 | REAR MOUNTED WASH MANIFOLD AND PROCESS - An engine wash manifold delivers wash liquid to an engine that includes an inlet, a fan, a case with an exhaust duct and a core inlet splitter. The manifold includes a wash delivery segment comprising a pipe shaped to follow at least in part engine case curvature with a first end to interface with the core inlet splitter and a second end with an inlet to receive wash fluid. The manifold further includes a retention system to secure the wash delivery segment to the engine and one or more nozzles on the first end of the wash delivery segment to spray wash fluid. The wash fluid may be atomized. The manifold further may include nozzles that deliver atomized wash liquid to the aft side of fan blades and may be used in conjunction with an inlet mounted manifold. | 09-18-2014 |
20140260308 | REAR MOUNTED WASH MANIFOLD RETENTION SYSTEM - A retention system includes a structure clamp to connect the retention system to another structure; and a manifold clamp connected to the structure clamp, the manifold clamp including a trough to receive a pipe, a plurality of tube clamps with split cylinders extending through the trough, a collar to clamp around the pipe, and a spring to bias the trough from the collar. | 09-18-2014 |
20140311156 | COMBUSTOR CAP FOR DAMPING LOW FREQUENCY DYNAMICS - A combustor cap for use with a number fuel nozzles, the combustor cap including a cold side plate, a hot side plate, and a cap cavity extending between the cold side plate and the hot side plate with the number of fuel nozzles extending therethrough. A resonator tube may extend from the cold side plate into the cap cavity. | 10-23-2014 |
20140345292 | RETURN FLUID AIR COOLER SYSTEM FOR TURBINE COOLING WITH OPTIONAL POWER EXTRACTION - In an aircraft including a gas turbine engine, a system for cooling the gas turbine engine includes a tank provided in a wing of the aircraft, the tank being configured to store a cooling fluid supply; and a heat exchanger provided in the gas turbine engine configured to exchange heat from the compressor discharge air to the cooling fluid. | 11-27-2014 |
20140366552 | METHOD AND DEVICE FOR SUPPRESSING THE FORMATION OF ICE ON STRUCTURES AT THE AIR INTAKE OF A TURBOMACHINE - The application relates to a method and a device for suppressing ice formation on intake structures of a compressor, particularly the compressor of a gas turbine. The technical aim of the present invention is to provide a method and a device for suppressing the formation of ice on said structures, which avoid the disadvantages of known solutions, such as a reduction of the performance of the gas turbine, and have a simple and broad applicability. According to the present invention the mechanical vibratory energy of said structures during operation is converted into electrical energy by a piezoelectric element, firmly applied to said structure, and in a connected electrical circuit the generated electrical energy is then converted into thermal energy by an ohmic resistor and this thermal energy is conducted to at least a portion of the structure for suppressing ice formation. Excess energy may be transmitted by a transmitter to other circuits in adjacent structures. | 12-18-2014 |
20140366553 | COMBUSTION CHAMBER FOR A GAS TURBINE AND GAS TURBINE AND A METHOD OF USE - A combustion chamber ( | 12-18-2014 |
20150013343 | METHOD AND DEVICE FOR SAFELY OPERATING A GAS TURBINE PLANT - A method and a device are disclosed for the safe operation of a gas turbine plant, whose operation is both controlled by at least one process controller, which at least triggers and/or influences operationally relevant processes of the gas turbine plant, and is also monitored by a separate protection unit that is operated independently of the process controller on the basis of at least one first limit value for a safety-relevant operating parameter, wherein the gas turbine plant is subjected to an emergency switch-off once the at least one first limit value is exceeded. In that in the case of a defined transient operating state of the gas turbine plant that can be detected by the protection unit, the at least one first limit value of the safety-relevant operating parameter is raised to a second limit value, wherein the gas turbine plant is protected by an emergency switch-off of the gas turbine plant once said second limit value is exceeded. Furthermore, secondary protective functions can be carried out in the process controller. | 01-15-2015 |
20150040577 | SYSTEM AND METHOD FOR PREVENTING ICE CRYSTAL ACCRETION IN GAS TURBINE ENGINES - A system and method of operating an engine anti-ice system includes supplying heat from one or more heat sources to one or more components on or within a gas turbine engine, sensing data representative of one or more parameters related to ice crystal accretion, and based on the data, at least selectively inhibiting at least selected ones of the one or more heat sources from supplying heat to at least selected ones of the one or more components on or within the gas turbine engine. | 02-12-2015 |
20150040578 | DEVICE AND METHOD FOR GAS TURBINE UNLOCKING - An aeroderivative gas turbine including an air intake plenum; a compressor with a compressor air intake in fluid communication with the air intake plenum; a combustor; a high pressure turbine; a power turbine. A forced air-stream generator is arranged in fluid communication with the air intake plenum. A shutter arrangement is provided in a combustion-air flow path, arranged and controlled to close the combustion-air flow path for pressurizing said air intake plenum by means of the forced air-stream generator to a pressure sufficient to cause pressurized air to flow through the aeroderivative air turbine. | 02-12-2015 |
20150047366 | OPERATION OF GAS TURBINE POWER PLANT WITH CARBON DIOXIDE SEPARATION - The invention relates to a method for operating a gas turbine power plant, including a gas turbine, a HRSG following the gas turbine, an exhaust gas blower, and a carbon dioxide separation plant which separates the carbon dioxide contained in the exhaust gases and discharges it to a carbon dioxide outlet, the gas turbine, HRSG, exhaust gas blower, and carbon dioxide separation plant being connected by means of exhaust gas lines. According to the method a trip of the gas turbine power plant includes the steps of: stopping the fuel supply, switching off the exhaust gas blower, and controlling the opening angle of a VIGV at a position bigger or equal to a position required to keep a pressure in the exhaust gas lines between the HRSG and the exhaust gas blower above a minimum required pressure. The invention relates, further relates to a gas turbine power plant configured to carry out such a method. | 02-19-2015 |
20150068216 | SYSTEM FOR INDUCTIVE HEATING OF TURBINE ROTOR DISKS - A turbine rotor with at least one rotor disk is provided. The turbine rotor includes a heating arrangement for heating at least a part of the rotor disk. The heating arrangement has a conductor for conducting electric current. The conductor is positioned such that in presence of the electric current in the conductor, Eddy current is generated in the part of the rotor disk. The electric current is an alternating current. The Eddy currents so generated in the part of the rotor disk result in inductive heating of the part of the rotor disk. | 03-12-2015 |
20150082802 | TURBOMACHINE COMPRISING A MONITORING SYSTEM COMPRISING A MODULE FOR ENGAGING A PROTECTION FUNCTION OF THE TURBOMACHINE AND MONITORING METHOD - An aircraft turbine engine comprising at least one spool rotating at speed N | 03-26-2015 |
20150101343 | GAS TURBINE COMBUSTOR - A gas turbine combustor is provided with a combustor basket where combustion gas flows, the combustion gas being produced by combustion of fuel injected from a nozzle, and a first resonance device and a second resonance device mounted on an outer surface of the combustor basket. The second resonance device is disposed on a downstream side from the first resonance device in a flow of the combustion gas and damps combustion oscillation of a frequency higher than the first resonance device. The first and second resonance devices are acoustic liners each having a housing mounted to the outer surface of the combustor basket. A resonance space surrounded by the housing and the outer surface of the combustor basket communicates with an interior space of the combustor basket via a plurality of acoustic holes formed in the combustor basket. | 04-16-2015 |
20150121894 | BIFURCATION FIRE PURGE SYSTEM - A bifurcation assembly for a gas turbine engine is disclosed and includes a housing defining an inner cavity. A first partition and a second partition extend across the inner cavity and define a buffer area therebetween. Openings through the first and second partitions define passageway for supply conduits. A control device governs the flow of a purge gas into the buffer area for blocking the spread of fire. The purge gas provides a barrier to the spread of fire and heat through the bifurcation assembly. | 05-07-2015 |
20150308286 | FRANGIBLE MOUNTING ARRANGEMENT AND METHOD FOR PROVIDING SAME - A frangible mounting arrangement between a bearing and a bearing support in a gas turbine engine comprises a plurality of frangible bolts connecting mounting flanges of the bearing and the bearing support. The plurality of frangible bolts is disposed on a circle. A distance on the circle between a first pair of adjacent frangible bolts is greater than a distance on the circle between a second pair of adjacent frangible bolts. The frangible bolts are resistant to axial loads and being configured to break when subjected to a breaking load above a predetermined value. The breaking load results from at least one of a bending moment and a shear load on the mounting flanges. When subjected to the breaking load, the first pair of adjacent frangible bolts breaking before the second pair of adjacent frangible bolts. A method of providing a frangible mounting arrangement between a bearing and a bearing support in a gas turbine engine is also provided. | 10-29-2015 |
20150337735 | METHOD OF PURGING A COMBUSTOR - A method of purging a combustor is provided. The method includes opening an isolation valve configured to regulate a flow rate of a fluid sent to at least one fuel nozzle of a combustor. The method also includes opening a control valve located upstream of the isolation valve after opening the isolation valve, wherein the isolation valve and the control valve are located within a fluid supply line. | 11-26-2015 |
20150345390 | SYSTEMS AND METHODS FOR DE-ICING INLET SCREENS AND DEHUMIDIFYING INLET AIR FILTERS FOR GAS TURBINE ENGINES - Systems and methods for de-icing an inlet screen and dehumidifying an inlet air filter in a gas turbine engine are disclosed herein. In one embodiment, a method may include determining a current inlet screen temperature. The method also may include determining a desired inlet screen temperature. If the current inlet screen temperature is less than the desired inlet screen temperature, the method may further include determining a first amount of gas turbine compartment ventilation discharge air necessary to achieve the desired inlet screen temperature, extracting the first amount of gas turbine compartment ventilation discharge air, and conveying the first amount of gas turbine compartment ventilation discharge air to the inlet screen. | 12-03-2015 |
20150377130 | Integrated Thermal Management with Nacelle Laminar Flow Control for Geared Architecture Gas Turbine Engine - A thermal management system for a gas turbine engine includes a heat exchanger in fluid communication with a geared architecture and a heating compartment. | 12-31-2015 |
20150377149 | AUTOMATIC COMBUSTION SYSTEM CHARACTERIZATION - Aspects of the present disclosure relate generally to a system including: a computing device in communication with a combustion system, wherein the computing device is configured to perform actions including: issuing an input to the combustion system; determining whether one of a dynamic output and an emission output corresponding to the input to the combustion system exceeds a first boundary condition; and adjusting the input to the combustion system by one of a first step change and a second step change; wherein the first step change corresponds to the dynamic output and the emission output not exceeding the first boundary condition, and the second step change corresponds to one of the dynamic output and the emission output exceeding the first boundary condition, the second step change being less than the first step change. | 12-31-2015 |
20160032836 | FILTRATION SYSTEM FOR A GAS TURBINE AIR INTAKE AND METHODS - A gas turbine air filter system includes a housing having an interior, an inlet arrangement, and an outlet hood having an outlet arrangement. The inlet arrangement defines an inlet flow face for taking in unfiltered air. The outlet arrangement defines an outlet flow face for exiting filtered air. The inlet flow face and the outlet flow face are angled relative to each other. The angle can range between 45-135° relative to each other. The system includes at least first and second stages of filter element arrangements held within the interior of the housing. The first and second stages of filter element arrangements are operably sealed within the housing such that air flowing through the inlet arrangement must pass through the first and second stages of filter element arrangements before exiting through the outlet arrangement. The outlet hood is free of the first and second stages of filter element arrangements. | 02-04-2016 |
20160076455 | METHOD AND SYSTEM TO PROTECT A SURFACE FROM CORROSIVE POLLUTANTS - Disclosed herein are systems and methods for protecting a surface from corrosive pollutants. A method includes detecting airborne corrosive pollutants proximate to a surface using at least one sensor adapted to detect a concentration of the airborne corrosive pollutants and/or one or more types of airborne corrosive pollutants, the concentration of the airborne corrosive pollutants being an instantaneous concentration value or a time-weighted-integrated concentration value; selecting a fluid to deliver to at least a portion of the surface based upon a predetermined type and/or concentration of the airborne corrosive pollutants detected by the at least one sensor; and initiating a fluid treatment to deliver the selected fluid such that the selected fluid contacts the at least a portion of the surface. | 03-17-2016 |
20160076766 | COMBUSTION SYSTEM OF A FLOW ENGINE AND METHOD FOR DETERMINING A DIMENSION OF A RESONATOR CAVITY - A combustion system of a flow engine has at least one combustion chamber, a shared manifold to feed a flow medium via at least two injectors to the at least one combustion chamber and at least one resonator with at least one resonator cavity, wherein the at least one resonator is arranged functionally in/at the manifold. To obtain good combustion performance with a homogenous fuel flow rate and high combustion stability, the resonator includes at least one perforated section with at least two orifices, wherein the at least two orifices provide access to the at least one resonator cavity of the at least one resonator. | 03-17-2016 |
20160123183 | METHOD FOR TESTING AN OVERSPEED PROTECTION MECHANISM OF A SINGLE-SHAFT COMBINED-CYCLE PLANT - A method for testing an overspeed protection mechanism of a single-shaft combined-cycle plant that includes, during testing, an electrical load is first connected to the generator and the load is disconnected and a trigger threshold value can be achieved at a test moment in time, thereby triggering the overspeed protection mechanism. | 05-05-2016 |
20160131036 | THERMAL MANAGEMENT SYSTEM FOR A GAS TURBINE ENGINE - In one exemplary embodiment, a gas turbine engine system for cooling engine components includes an engine core, a core housing containing the engine core, an engine core driven fan forward of the core housing, a nacelle surrounding the fan and the core housing, and a bypass duct defined between an outer diameter of the core housing and an inner diameter of the nacelle. Also included is a thermal management system having a coolant circuit including at least one of a first heat exchanger disposed on the inner diameter of the nacelle and a second heat exchanger disposed on a leading edge of a BiFi spanning the bypass duct. The first heat exchanger is in thermal communication with the second heat exchanger. | 05-12-2016 |
20160153656 | COMBUSTION CONTROL DEVICE, COMBUSTION SYSTEM, COMBUSTION CONTROL METHOD AND PROGRAM | 06-02-2016 |
20160160758 | GAS TURBINE ENGINE NACELLE ANTI-ICING SYSTEM - A gas turbine engine de-icing system includes a heat exchanger. A coolant loop is in fluid communication with the heat exchanger and is configured to circulate a coolant. An engine oil loop is in fluid communication with the heat exchanger and is configured to transfer heat to the coolant. A gas turbine engine inlet structure includes a cavity. A manifold is arranged in the cavity and is in fluid communication with the coolant loop. The manifold is configured to spray the coolant onto the gas turbine engine inlet structure to de-ice the gas turbine engine inlet structure. | 06-09-2016 |
20160177824 | GAS TURBINE ENGINE INTAKE DUCT | 06-23-2016 |
20160177878 | METHOD AND SYSTEM FOR A GAS TURBINE ENGINE AIR VENTILATION PURGE CIRCUIT | 06-23-2016 |
20160177879 | METHOD AND SYSTEM FOR A GAS TURBINE ENGINE PURGE CIRCUIT WATER INJECTION | 06-23-2016 |
20160252251 | METHOD AND DEVICE FOR FLAME STABILIZATION IN A BURNER SYSTEM OF A STATIONARY COMBUSTION ENGINE | 09-01-2016 |
20170234166 | BOWED ROTOR PREVENTION SYSTEM USING WASTE HEAT | 08-17-2017 |