Rolls-Royce Corporation Patent applications |
Patent application number | Title | Published |
20160137559 | COMPLIANT LAYER FOR CERAMIC COMPONENTS AND METHODS OF FORMING THE SAME - An apparatus includes a ceramic matrix composite (CMC) component and an interface coating on the CMC component, wherein the interface coating includes a layer of at least one of the following compositions: 100 wt % Ir; 90-95 wt % Ir, 5-10 wt % Co, 1-2 wt % Al, 1-2 wt % Si; 40-50 wt % Nb, 28-42 wt % Al, 4-15 wt % Cr, 1-2 wt % Si; 90-92 wt % Mo, 4-5 wt % Si, 4-5 wt % B; or 60-80 wt % V, 20-30 wt % Cr, 2-15 wt % Ti. | 05-19-2016 |
20160096629 | TRANS-CRITICAL VAPOR CYCLE SYSTEM WITH IMPROVED HEAT REJECTION - A cooling system for an aircraft includes an air intake, an expansion device, and an evaporator. A first heat exchanger receives air passing into the air intake when the aircraft is operating at elevation, and receives the refrigerant from a first compressor at a first pressure. A second compressor receives the refrigerant from the first heat exchanger and compresses the refrigerant to a second pressure that is greater than the first pressure. A second heat exchanger receives the refrigerant from the second compressor. The first and second compressors are configured the first and second compressors are configured to operate at pressures that avoid temperature differences between the refrigerant and the air within each of the first and second heat exchangers below a set restriction. | 04-07-2016 |
20160070253 | MONITORING HOLE MACHINING - A method includes machining a component with a machine tool to form a feature in the component, monitoring, by a computing device, while machining the feature into the component with the machine tool, horsepower of the machine tool used to machine the component, determining, by the computing device, a quality of the feature in the component based on the monitored horsepower, and storing, by the computing device, an indication of the quality of the feature in combination with a unique identifier for the feature in a non-transitory computer-readable medium. | 03-10-2016 |
20160003052 | DAMAGE TOLERANT COOLING OF HIGH TEMPERATURE MECHANICAL SYSTEM COMPONENT INCLUDING A COATING - An article may include a substrate, a plurality of cooling holes in the substrate, wherein each of the plurality of cooling holes defines substantially the same diameter measured parallel to an outer surface of the substrate, and a coating on the surface of the substrate. In accordance with these examples, the coating covers and substantially blocks a first set of cooling holes from the plurality of cooling holes and leaves a second set of cooling holes from the plurality of cooling holes substantially uncovered. In some examples, an article including a substrate, a plurality of cooling holes in the substrate, and a coating on the substrate. In accordance with these examples, the coating covers and partially occludes each cooling hole of the plurality of cooling holes, and the coating does not extend into any of the plurality of cooling holes. | 01-07-2016 |
20150354936 | COMPONENT INCLUDING STRUCTURES FOR DETERMINANT LOADING - An apparatus including a first component having an exterior surface formed of a ceramic material and including a primary surface region and a plurality of secondary surface regions protruding from the primary surface region, and a second component positioned in contact with at least one of the secondary surface regions and spaced from the primary surface region to define a determinant load path between the first and second components. A method of forming the apparatus is also provided. | 12-10-2015 |
20150040576 | COUNTER SWIRL DOUBLET COMBUSTOR - An improved combustor for a gas turbine is operable to provide high combustion efficiency in a compact combustion chamber. The combustor includes a counter swirl doublet for improved fuel/air mixing. The enhanced combustor assembly and method of operation improves operation of the turbine. | 02-12-2015 |
20150040538 | ROTOR NOISE SUPPRESSION - An apparatus is disclosed that includes a gas turbine engine including a first rotor blade axially adjacent a second rotor blade and an aperture formed in one of the first rotor blade and the second rotor blade and structured to emit a fluid therefrom. A fluid source is in flow communication with the aperture and configured to flow the fluid through the aperture. | 02-12-2015 |
20150014994 | VEHICLE RECUPERATOR - An engine may have a recuperator that may be powered by an electrical generator driven by the engine. The recuperator may be disposed within or incorporated into a compressor discharge of the engine, such as in the form of a vane or tube. The engine may be configured to operate in a variety of modes at least some of which may use thermal energy from the recuperator to heat a fluid flow stream of the engine. An energy storage device may be used with an electrical generator to provide power to a load. | 01-15-2015 |
20150013340 | GAS TURBINE ENGINE COMBUSTOR LINER - A gas turbine engine variable porosity combustor liner has a laminated alloy structure. The laminated alloy structure has combustion chamber facing holes on one side and cooling plenum facing holes on a radially opposite side. The combustion chamber facing holes are in fluid communication with the cooling plenum facing holes via axially and circumferentially extending flow passages sandwiched between metal alloy sheets of the laminated alloy structure. Porous zones having respective different cooling flow amounts are formed in the laminated allow structure based on at least one of an arrangement of the combustion chamber facing holes, an arrangement of the cooling plenum facing holes, and an arrangement of the flow passages. | 01-15-2015 |
20140366563 | ADAPTIVE TRANS-CRITICAL CO2 COOLING SYSTEMS FOR AEROSPACE APPLICATIONS - A cooling system includes a heat exchanger through which a refrigerant flows, and which rejects heat to a fluid, an evaporator, a first circuit having an expansion device, a second circuit having an expansion machine coupled to a compressor, and a set of valves arranged to direct the refrigerant through the first circuit, the second circuit, or both the first and second circuits based on ambient conditions. | 12-18-2014 |
20140363276 | ULTRA HIGH BYPASS RATIO TURBOFAN ENGINE - An ultra high bypass ratio turbofan engine includes a variable pitch fan, a low pressure turbine, a reduction gearbox, and a plurality of outlet guide vanes. The ultra high bypass ratio turbofan engine has a bypass ratio between about 18 and about 40. The variable pitch fan and the low pressure turbine are coupled together by the reduction gearbox. The reduction gearbox reduces the speed of the variable pitch fan relative to the low pressure turbine. The plurality of outlet guide vanes are spaced aft of the variable pitch fan and are axially swept. The variable pitch fan and the low pressure turbine are configured to generate a fan pressure ratio between about 1.15 and about 1.24. | 12-11-2014 |
20140360205 | GAS TURBINE ENGINE AND ELECTRICAL SYSTEM - One embodiment of the present disclosure is a unique gas turbine engine. Another embodiment of the present disclosure is a unique machine. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for gas turbine engines and electrical systems. | 12-11-2014 |
20140352323 | FLEXIBLE BELLOWS IGNITER SEAL - A flexible bellows assembly is disclosed for sealing an engine igniter for use with an engine. The bellows assembly includes a mounting arrangement that is operable to be secured to a combustor diffuser instead of the combustor liner. The bellows has a component that impinges upon a surface of the combustor liner so as to form a sealed chamber between a metal diffuser and a ceramic combustion liner. An igniter passes through the sealed chamber and provides ignition to the combustor. | 12-04-2014 |
20140352275 | INVERTED CAP IGNITER TUBE - An igniter tube assembly includes an igniter, an igniter tower with a radially extending portion, a ferrule with a radially extending portion, and a retainer with a radially extending portion. The ferrule and retainer capture the radially extending portion of the igniter tower and sealing surface provides an area for the ferrule to interface with the igniter tower. The igniter moves relative to the casing in which it is secured while a fluid seal between the igniter and ferrule controls air flow. | 12-04-2014 |
20140311153 | COMBUSTOR ASSEMBLY FOR A GAS TURBINE ENGINE - A combustor assembly for a gas turbine engine includes a hanger and a combustor liner fixed to the hanger such as, for example, by an annular weld joint. The combustor liner has an inner surface extending along an axis and is operable to define either a radial outer boundary or a radial inner boundary of the combustion chamber. The combustor assembly also includes a heat shield at least partially overlapping and confronting the inner surface of the combustor liner along the axis, with the heat shield releasably engaged with the hanger. | 10-23-2014 |
20140308113 | STRUCTURE AND METHOD FOR PROVIDING COMPLIANCE AND SEALING BETWEEN CERAMIC AND METALLIC STRUCTURES - A structure providing compliance and sealing between ceramic or ceramic composite (CMC) part and a metallic part has an interface component for centering the CMC part in the metallic part, thus reducing thermal stress motion of the CMC component. In gas turbine engine applications, the structure comprises a CMC blade track inserted in a clip placed within a metallic hanger. The clip provides for radial compliance and secures controlled leakage of cooling air required to ensure that acceptable temperatures are maintained for the metallic structures. A washer is positioned adjacent to the clip provide for axial orientation of the blade track. | 10-16-2014 |
20140284848 | METHOD AND APPARATUS ASSOCIATED WITH ANISOTROPIC SHRINK IN SINTERED CERAMIC ITEMS - A manufacturing method for producing ceramic item from a photocurable ceramic filled material by stereolithography. The method compensates for the anisotropic shrinkage of the item during firing to produce a dimensionally accurate item. | 09-25-2014 |
20140277992 | INTEGRATED HEALTH MANAGEMENT APPROACH TO PROPULSION CONTROL SYSTEM PROTECTION LIMITING - A real-time engine management system having a controller system configured to control demand on a first component of an engine. The controller system is also configured to access a first set of prognostic data about the first component, where the first set of prognostic data includes a remaining lifespan approximation of the first component operating at a present operating condition. The controller system is also configured to identify a temporal length of an engine procedure operating at the present operating condition, alter a current limit constant associated with the first component to increase the remaining lifespan approximation of the first component beyond the temporal length, and implement the current limit constant associated with the first component so that the first component does not fault during the engine procedure. | 09-18-2014 |
20140273681 | SIC BASED CERAMIC MATRIX COMPOSITES WITH LAYERED MATRICES AND METHODS FOR PRODUCING SIC BASED CERAMIC MATRIX COMPOSITES WITH LAYERED MATRICES - Ceramic matrix composites include a fiber network and a matrix including layers of first and second materials. The first material may include SiC. The second material may include an element that when oxidized forms a silicate that is stable at high temperatures. | 09-18-2014 |
20140272431 | LAYERED DEPOSITION FOR REACTIVE JOINING OF COMPOSITES - A method including applying layers of multiple constituents where the constituents are capable of producing a non-equilibrium condition on the contacting surfaces of a ceramic matrix composite component and a gas turbine engine component where one outer coating includes a first constituent and the other outer coating includes a second constituent; forming a component assembly with the ceramic matrix composite component coupled to the gas turbine engine component with contact between the outer coatings; adding an energy to facilitate an equilibrium reaction between the first constituent of the first outer coating and the second constituent of the second outer coating; and as a result of adding the energy, forming a bond structure in the component assembly with a product of the equilibrium reaction where the bond structure affixes the ceramic matrix composite component to the gas turbine engine component between the first constituent and the second constituent. | 09-18-2014 |
20140272377 | REACTIVE MELT INFILTRATED-CERAMIC MATRIX COMPOSITE - A method includes providing a ceramic fiber preform with a range of 20 to 40 volume percent fiber which can include silicon carbide fibers; coating the ceramic fiber preform with a boron nitride interface coating; infiltrating the ceramic fiber preform with a ceramic matrix with a range of 20 to 40 volume percent silicon carbide; infiltrating the ceramic fiber preform with a constituent material such as boron carbide, boron, and carbon; and infiltrating the ceramic fiber preform with a eutectic melt material where the metallic eutectic melt can include at least one material from a group consisting of: a transition metal-silicon eutectic melt such as zirconium silicide, a transition metal-boride eutectic melt such as zirconium boride, and a transition metal-carbide eutectic melt such as zirconium carbide. | 09-18-2014 |
20140272310 | COATING INTERFACE - In one example, article comprising a substrate defining an outer surface; a plurality of joint conduits formed in the outer surface of the substrate, wherein each conduit of the plurality of joint conduits exhibits an undercut configuration; and a coating formed on the outer surface of the substrate, wherein the coating substantially fills the plurality of joint conduits formed in the surface of the substrate. | 09-18-2014 |
20140272274 | HIGH STRENGTH JOINTS IN CERAMIC MATRIX COMPOSITE PREFORMS - A joint between a first preform component and a second preform component that are constructed for ultimate use in a gas turbine engine is disclosed. A plurality of extended fibers may be integral with the first preform component and be at least partially enveloped by the second preform component. A method for making the component is also disclosed. In one embodiment the method provides a first preform component having extended fibers integral therewith, and supplying a second preform component. The method further includes inserting the extended fibers at least partially into the second preform component body. | 09-18-2014 |
20140272249 | SLURRY-BASED COATING RESTORATION - In some examples, a method includes identifying a damaged area in a ceramic matrix composite coating of an in-service component; applying a restoration slurry to the damaged area of the ceramic matrix composite coating, wherein the restoration slurry comprises a liquid carrier and a restoration coating material; drying the restoration slurry to form a dried restoration slurry; and heat treating the dried restoration slurry to form a restored portion of the ceramic matrix composite coating. In some examples, an assembly may include a component including a substrate and a coating on the substrate, where the coating defines a damaged portion; masking around the damaged portion on undamaged portions of the coating; and a restoration slurry in the damaged portion, wherein the restoration slurry comprises a liquid carrier and a restoration coating material. | 09-18-2014 |
20140272248 | CERAMIC MATRIX COMPOSITE REPAIR BY REACTIVE PROCESSING AND MECHANICAL INTERLOCKING - A method for modifying a ceramic matrix component is disclosed including identifying a non-conforming region of a composite component capable of operating in a gas turbine engine; removing at least a portion of the non-conforming region to create an exposed surface of the composite component; preparing a preform in response to the removing at least a portion of the non-conforming region; applying a reactive constituent surface region to at least one of the exposed surface of the composite component and the preform, the reactive constituent surface region being capable of producing a non-equilibrium condition; positioning the preform to provide a contact region between the exposed surface of the composite component and the preform proximate the reactive constituent surface region; and reacting the reactive constituent surface region in an equilibrium reaction at the contact region to form a bond structure between the exposed surface of the composite component and the preform. | 09-18-2014 |
20140272246 | TEXTILE MATERIAL JOINING TECHNIQUES - Techniques for joining textile materials are provided. In one non-limiting form, a system includes a woven structure having a first woven layer and at least a first section and a second section. The first section includes a first fringe portion and a first set of fibers, and the second section includes a second fringe portion and a second set of fibers. The fibers of the first and second sets of fibers are configured in the first and second fringe portions to provide an interlocking arrangement between the first and second sections. Further embodiments, forms, features, and aspects shall become apparent from the description and drawings. | 09-18-2014 |
20140272197 | DIRECTED VAPOR DEPOSITION OF ENVIRONMENTAL BARRIER COATINGS - In some examples, a method may include directing an electron beam at a coating source to create a vapor plume, wherein the coating source comprises alumina and at least one rare earth oxide. The method also may include transporting the vapor plume using a gas stream provided adjacent to the coating source to within an internal cavity defined by a surface of a substrate of a gas turbine engine blade, vane, blade track, or combustor liner, and wherein the substrate comprises at least one of a silicon-containing ceramic or a ceramic matrix composite. Additionally, the method may include depositing the alumina and the at least one rare earth oxide from the vapor plume over the surface of the internal cavity to form a calcia-magnesia-alumina-silicate (CMAS)-resistant environmental barrier coating (EBC) comprising the alumina and the at least one rare earth oxide. | 09-18-2014 |
20140271161 | CERAMIC MATRIX COMPOSITE - A novel ceramic matrix composite is disclosed for forming components that are operable in high temperature environments such those in gas turbine engines and the like. The ceramic matrix composite can include at least one layer of non-crimped fibers positioned substantially parallel to one another. A relatively small diameter elastic fiber can be constructed to stitch the non-crimped fibers together and a ceramic matrix may be deposited around the at least one layer of non-crimped fibers. | 09-18-2014 |
20140271113 | MODULATED COOLING FLOW SCHEDULING FOR BOTH SFC IMPROVEMENT AND STALL MARGIN INCREASE - A turbine engine includes a compressor, and high and low pressure turbines. The configuration includes a mid-compression station which can be, in the case of a single compressor in the middle of that compressor, or at the exit of the first compressor in the case of two compressors. Also, there is an exit pressure station at the exit of the compression system. A first gas flow line is interposed between the mid-compression station of the compressor and the low pressure turbine, and a second gas flow line is interposed between the exit pressure station of the compression system and the high pressure turbine. A first valve is coupled to the first gas flow line and modulates a low pressure flow rate of coolant in the first gas flow line, and a second valve is coupled to the second gas flow line and modulates a high pressure flow rate of coolant in the second coolant flow line. A controller is configured to operate the first and second valves based on an operating condition of the turbine engine so as to improve the specific fuel consumption while ensuring acceptable stall margin. | 09-18-2014 |
20140267694 | NONDESTRUCTIVE TESTING OF A COMPONENT - In some examples, a method for nondestructive testing of a component may include flashing the component using a flash lamp configured for flash thermography, collecting first image data regarding the component using an infrared camera, flowing a fluid through the component, and collecting second image data regarding the component using the infrared camera. A system for nondestructive testing of a component may include a single inspection station and a flash lamp configured for flash thermography, means for supplying a fluid to the component, and an infrared camera disposed at the inspection station. | 09-18-2014 |
20140261986 | METHOD FOR MAKING GAS TURBINE ENGINE COMPOSITE STRUCTURE - A method for making a gas turbine engine matrix composite structure. The method includes providing at least one metal core element, fabricating a matrix composite component about the metal core element, and removing at least part of the metal core element from the matrix composite component by introduction of a halogen gas. | 09-18-2014 |
20140261080 | RARE EARTH SILICATE ENVIRONMENTAL BARRIER COATINGS - A vapor deposition method may include applying a first electron beam to vaporize a portion of a first target material comprising a rare earth oxide, where the first electron beam delivers a first amount of energy. The method also may include applying a second electron beam to vaporize a portion of a second target material comprising silica, where the second electron beam delivers a second amount of energy different from the first amount of energy. In some examples, the second target material is separate from the first target material. Additionally, the portion of the first target material and the portion of the second target material may be deposited substantially simultaneously over a substrate to form a layer over the substrate. A system for practicing vapor deposition methods and articles formed using vapor deposition methods are also described. | 09-18-2014 |
20140260341 | ADAPTIVE TRANS-CRITICAL CARBON DIOXIDE COOLING SYSTEMS - A cooling system includes a first heat exchanger, an evaporator coupled to a thermal load of an aircraft. first and second cooling circuits coupled to the heat exchanger, the first and second cooling circuits selectable via a set of cooling circuit valves that are arranged to direct a refrigerant through the first circuit, the second circuit, or both the first and second circuits based on air passing through the first heat exchanger at ambient conditions of the aircraft, and a receiver configured to accumulate reserve refrigerant to provide flexibility in system operation as the cooling system operates in sub-critical, trans-critical, and super-critical modes of operation. | 09-18-2014 |
20140260340 | ADAPTIVE TRANS-CRITICAL CO2 COOLING SYSTEMS FOR AEROSPACE APPLICATIONS - A cooling system for an aircraft includes a first cooling circuit having a first evaporator and a second evaporator, and a second cooling circuit having a third evaporator and a fourth evaporator. One of the first and second cooling circuits includes a first set of valves arranged to direct refrigerant through a first cooling sub-circuit, a second cooling sub-circuit, or both the first and second cooling sub-circuits based on ambient conditions. Two of the evaporators are installed on a first side of the aircraft, and the other two of the four evaporators are installed on a second side of the aircraft opposite the first side, and the first and second cooling circuits reject heat, via a heat exchanger, from their respective cooling circuit to air passing into an engine of the aircraft. | 09-18-2014 |
20140260320 | BI-METAL FASTENER FOR THERMAL GROWTH COMPENSATION - An improved fastening system and method overcomes traditional thermal mismatch that occurs with standard fastener systems that are employed in extreme temperature environments. The fastening system could employ a metallic fastener that is combined with metallic spacer, each of which having a differing thermal growth coefficient. This arrangement may reduce thermal expansion by several orders of magnitude over the range of temperatures where the thermal fastener can be applied. Such an improved fastening system may be employed in gas turbine machines and in other locations where it is desirable to improve fastening of objects in extreme temperature environments. | 09-18-2014 |
20140260304 | ALGAE-DERIVED FUEL/WATER EMULSION - A method including providing a wet algae material having been subjected to a refinement process without a water separation phase; supplying the wet algae material including a water fraction and an algae-grown biofuel to a turbine engine; and operating the turbine engine with the wet algae material where a retained portion of the water fraction is retained in the wet biofuel during a manufacturing process not including a dehydration step and includes an amount sufficient to reduce generation of a quantity of nitrogen oxides, and where the turbine engine can further include a combustor capable of combusting the wet biofuel. | 09-18-2014 |
20140260290 | POWER-GENERATING APPARATUS AND METHOD - A power-generating apparatus includes a compressor section and a combustor section positioned downstream of the compressor section. The combustor section defines a combustion chamber operable to receive compressed fluid from the compressor section. The apparatus includes a turbine section positioned downstream of the combustor section operable to receive combustion gases from the combustion chamber and convert the combustion gases into kinetic energy. The apparatus also includes a waste container positioned downstream of the turbine section and exposed to the discharged exhaust gases. The waste container can hold waste material that receives the hot exhaust gas and combusts, further heating the exhaust gases. The apparatus also includes a conduit having an inlet fluidly communicating with the turbine section and receiving the exhaust gases. The apparatus also includes a heat exchanger operably disposed between the compressor section and the combustor section to heat the compressed fluid. | 09-18-2014 |
20140260289 | MULTI-PASSAGE DIFFUSER WITH REACTIVATED BOUNDARY LAYER - A diffuser is disclosed that includes a splitter having a blunt forebody useful in re-starting a boundary layer. The blunt forebody can be used to create a static pressure bow wave and interaction with a passing fluid stream that reduces a thickness of boundary layer formed on an opposing wall. The re-start in boundary layer can be used in a way that allows an upstream portion of the diffuser to be sized approaching a separation limit and a downstream portion of the diffuser to also be sized approaching a separation limit. In some forms the passages split by the blunt forebody can be sized relative to each other to balance flow between the branches. | 09-18-2014 |
20140260282 | GAS TURBINE ENGINE COMBUSTOR LINER - A gas turbine engine variable porosity combustor liner has a laminated alloy structure. The laminated alloy structure has combustion chamber facing holes on one side and cooling plenum facing holes on a radially opposite side. The combustion chamber facing holes are in fluid communication with the cooling plenum facing holes via axially and circumferentially extending flow passages sandwiched between metal alloy sheets of the laminated alloy structure. Porous zones having respective different cooling flow amounts are formed in the laminated alloy structure based on at least one of an arrangement of the combustion chamber facing holes, an arrangement of the cooling plenum facing holes, and an arrangement of the flow passages. | 09-18-2014 |
20140259589 | REPAIR OF GAS TURBINE ENGINE COMPONENTS - In some examples, a technique includes delivering, using a material delivery device, material adjacent to a repair surface of a component and delivering, using a gas delivery device, a gas adjacent to the repair surface. The technique also may include delivering, from an energy source, energy to the material adjacent the repair surface to fuse the material to the repair surface; and receiving, by a computing device, at least one parameter indicative of at least one of a temperature or a geometry of the component. The technique may further include, responsive to the at least one parameter indicative of the at least one of the temperature or the geometry of the component, controlling, by the computing device, at least one processing parameter to control the temperature of the component. | 09-18-2014 |
20140257551 | ADAPTIVE MACHINING OF COMPONENTS - In some examples, an adaptive machining system may include a model comparison unit, a compromise shape determination unit, and a program modification unit. The model comparison unit can be configured to compare electronic measured dimensional surface data of a component with an electronic surface model of the component. The compromise shape determination unit can be configured to determine a compromise shape for the component based on the comparison. The program modification unit can be configured to modify a machine tool program code based on the compromise shape. | 09-11-2014 |
20140257543 | ADAPTIVELY MACHINING COMPONENT SURFACES AND HOLE DRILLING - A method includes receiving a design surface data set, obtaining a component surface data set from the inspection of a component, creating a modified surface data set in response to the design surface data set and the component surface data set, generating a machining path in response to the modified surface data set, and machining the component in response to the machining path to produce a machined component according to the modified surface data set. The machined component deviates from the design surface data set. | 09-11-2014 |
20140255620 | SONIC GRAIN REFINEMENT OF LASER DEPOSITS - A metal additive method includes directing sonic and/or ultrasonic energy from a probe that is directed toward a melt pool during solidification of the melt pool and formation of a layer, wherein a solid portion of an object on which the pool is positioned at least partially surrounds the melt pool. | 09-11-2014 |
20140255204 | AERODYNAMIC FAIRINGS SECONDARILY ATTACHED TO NOSECONE - An aerodynamic fan nosecone for a gas turbine engine is provided and includes a fan nosecone that may be made of composite material. To improve airflow transition to the blade members, aerodynamic fairings are provided and are secured to an exterior surface of the nosecone which enhances fuel economy. The fairings may be secured to the nosecone by various methods, including providing for the fairings to be changed out and replaced with other fairings on the same nosecone assembly. | 09-11-2014 |
20140255152 | FAN TRACK LINER DESIGNED TO YIELD NEXT TO FAN CASE HOOK - A containment system for a gas turbine engine includes a fan track assembly for use with a containment case. The fan track assembly includes a body of collapsible material that is positioned within a cavity of the fan case, and voids are provided for providing space in the event of a catastrophic blade failure. Various configurations of the fan track liner assembly are provided along with various mounting methodologies for securing the track liner assembly to the fan case of a gas turbine engine. | 09-11-2014 |
20140253031 | WIRELESS BATTERY CHARGING SYSTEM - An inductive battery charger is incorporated with a power source that in one embodiment is a genset. A charging surface can be provided that in some forms is hinged, separable, or includes a pocket. In some forms resonant inductive coupling can be used to charge a battery through inductive charging. A battery can be charged within an area such as a perimeter of a military post (e.g. an observation post) using techniques described herein. A battery can also be charged remotely by inductive techniques such as through the use of a passing vehicle, etc. | 09-11-2014 |
20140252721 | SLOTTED LABYRINTH SEAL - A seal for use in a machine, such as a machine with rotating members, includes a labyrinth seal with multiple fins. The seal is slotted and is designed to limit fluid flow to the desired amount from the high pressure side of the seal to the low pressure side of the seal inside partially or exclusively radially extending cavities between two rotating members. The rotating members may operate at different speeds with a common axis of rotation. The seal remains effective when the rotating members move axially in relation to one another despite the fins having a component parallel to the axis of rotation. | 09-11-2014 |
20140250899 | GAS TURBINE ENGINE THERMALLY CONTROLLED FLOW DEVICE - An apparatus includes a gas turbine engine flow device having an inner member and a surrounding member. The inner member has a first coefficient of thermal expansion; and the surrounding member at least partially surrounds the inner member and has a second coefficient of thermal expansion that is different from the first coefficient of thermal expansion. The surrounding member includes at least two walls that form a variable flow gap therebetween. The inner member is oriented relative to the at least two walls of the surrounding member such that, based on the difference in the first and second coefficients of thermal expansion, the inner member expands relatively greater than the surrounding member or the surrounding member expands relatively greater than the inner member, according to a temperature change to correspondingly enlarge or reduce the size of the variable flow gap between the at least two walls. | 09-11-2014 |
20140250894 | DUAL-WALL IMPINGEMENT, CONVECTION, EFFUSION (DICE) COMBUSTOR TILE - A gas turbine engine includes a combustor having a dual-wall impingement convention effusion combustor tile assembly. The dual-wall tile assembly provides a cooling air flow channel and attachments for securing the tile to the cold skin liner of the combustor. Cooling is more efficient in part due to the dual wall construction and in part due to reduced parasitic leakage, and the design is less sensitive to attachment features which operate at lower temperatures. | 09-11-2014 |
20140250861 | AIRCRAFT POWER PLANT - An aircraft power plant is disclosed having a plurality of bladed rotors in flow communication driven by separate work producing devices. The work producing devices can take a variety of forms including an internal combustion engine and electric motor, for example. The bladed rotors can be associated with an aircraft pylon and can be driven independently to separate operating conditions to provide optimum performance. For example, the bladed rotors can be driven to separate operating conditions that improve a noise signature or performance of the aircraft. | 09-11-2014 |
20140250860 | MULTI-SHAFT GAS TURBINE ENGINE - A gas turbine engine is disclosed with a first spool having a first turbine connected to a first compressor through a first rotatable shaft; a second spool having a second turbine connected to a second compressor through a second rotatable shaft; and a gearbox having a power input port coupled to each of the first and second shafts and a power output port connected to a third shaft, wherein the rotational speed of the third shaft is lower than the rotational speed of each of the first and second shafts. | 09-11-2014 |
20140248121 | AIRCRAFT POWER SYSTEM - A gas turbine engine is disclosed which includes a bypass passage that in some embodiments are capable of being configured to act as a resonance space. The resonance space can be used to attenuate/accentuate/etc a noise produced elsewhere. The bypass passage can be configured in a number of ways to form the resonance space. For example, the space can have any variety of geometries, configurations, etc. In one non-limiting form the resonance space can attenuate a noise forward of the bypass duct. In another non-limiting form the resonance space can attenuate a noise aft of the bypass duct. Any number of variations is possible. | 09-04-2014 |
20140248120 | BI-METAL STRIP-SEAL - An improved seal assembly for use with a combustion liner assembly is employed with a gas turbine engine so as to control fluid flow. The seal assembly has a bi-metal sealing member that is affixed to a first surface that is proximal to a second perpendicular surface that is not in contact with the first surface, thus providing a potential fluid flow path. Upon heating, the bi-metal sealing member “uncoils” contacting the second perpendicular surface, thus blocking the flowpath between the two surfaces. Various metals may be provided to provide predetermined sealing characteristics. | 09-04-2014 |
20140241890 | GAS TURBINE ENGINE BLADE AND DISK - In some examples, an apparatus may include a gas turbine engine component comprising a blade, a platform forming an airflow surface from which the blade extends on one side, and a motion weld receiving surface disposed on a non-airflow side of the platform, and a disk having a motion weld disk portion to receive the motion weld receiving surface of the gas turbine engine component and form a motion weld coupling when the disk and gas turbine engine component are coupled, wherein, prior to coupling, the gas turbine engine component further includes a blade stalk disposed on the non-airflow side of the platform and in which is formed the motion weld receiving surface. | 08-28-2014 |
20140241850 | AIR PARTICLE SEPARATOR - A gas turbine engine is disclosed having a particle separator and an ejector disposed downstream of the particle separator and structured to entrain a dirty flow from the separator. A container of working fluid can be placed in flow communication with the ejector to provide an ejector flow to entrain the dirty flow from the particle separator. Alternatively and/or additionally, the ejector can be configured to use a flow of working fluid from the gas turbine engine as an ejector flow. | 08-28-2014 |
20140238097 | LAMINATED CAVITY TOOLING - In some examples, a laminated tooling die may include multiple sheets or plates used in conjunction in any of a number of forming operations such as, for example, hydroforming, compression molding, and stamping. The sheets or plates can include an open interior that, when used in conjunction with neighboring sheets, produce a cavity into which a deformable workpiece can be placed and subjected to the forming operation. In some examples, one or more sheets can be coupled with a heat exchanger to impart a heat transfer with the workpiece. | 08-28-2014 |
20140238040 | COMBINED CYCLE POWER PLANT - A combined cycle engine is used to provide power to a vehicle. In one form the combined cycle engine includes two engines coupled through a gearbox. The engines can include a gas turbine engine, reciprocating engine, and a rotary engine. In one embodiment the combined cycle engine includes a gas turbine engine coupled to a gearbox along with either a reciprocating or rotary engine also coupled to the gearbox. One or more clutches can be provided to selectively couple the gas turbine engine and the reciprocating or rotary engine to the vehicle through the gearbox. In one embodiment the diesel engine can provide power to the vehicle during an idle condition and then also provide power to the gas turbine engine to assist the starting of the gas turbine engine. | 08-28-2014 |
20140238037 | GAS TURBINE ENGINE AND METHOD FOR OPERATING A GAS TURBINE ENGINE - One embodiment of the present disclosure is a unique method for operating a gas turbine engine during flight operation of the gas turbine engine in an aircraft. Another embodiment of the present disclosure is a unique gas turbine engine. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for gas turbine engines. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith. | 08-28-2014 |
20140230972 | WALL MEMBER USEFUL IN QUENCHING - In some examples, an apparatus includes a pallet supporting a plurality of workpieces, the pallet including through-holes structured to pass a quenching fluid. In some examples, the apparatus further includes a reservoir of quenching fluid configured to provide the quenching fluid, and a plurality of upturned wall portions extending from the pallet and substantially surrounding the exteriors of the plurality of workpieces. The plurality of upturned wall portions may be located in relative orientation to the plurality of workpieces to regulate heat transfer coefficients of the plurality of workpieces during a quenching operation. | 08-21-2014 |
20140230212 | WELD REPAIR OF A COMPONENT - A method for repairing a component may include machining a depression into the component. A size and a shape of the depression may be configured to remove a damaged portion of the component; and wherein the depression forms a repair volume. The method also may include depositing a plurality of continuous additive weld layers, each continuous additive weld layer of the plurality of continuous additive weld layers having a beginning point and an ending point. The beginning point and the ending point of a first continuous additive weld layer of the plurality of additive weld layers may be formed at or beyond an outer boundary of the repair volume. The beginning points and the ending points of the remainder of the plurality of continuous additive weld layers may be formed at or beyond the outer boundary of the repair volume. | 08-21-2014 |
20140147696 | ALLOY WITH ION BOMBARDED SURFACE FOR ENVIRONMENTAL PROTECTION - An article may include a substrate that comprises a nickel alloy. The substrate may include a modified subsurface region and a bulk region. The modified subsurface region may include a first composition and the bulk region may include a second composition different than the first composition. The modified subsurface region may include at least one of a reactive element or a noble metal, and the modified subsurface region comprises a thickness of less than about 0.3 μm measured in a direction substantially normal to a surface of the substrate. The modified subsurface region may be formed by depositing a layer including at least one of the reactive element or the noble metal in a layer on a surface of the substrate and introducing the at least one of the reactive element or the noble metal into the modified subsurface region using ion bombardment. | 05-29-2014 |
20140134455 | INTERFACIAL DIFFUSION BARRIER LAYER INCLUDING IRIDIUM ON A METALLIC SUBSTRATE - An article may include a substrate, a diffusion barrier layer formed on the substrate, and a protective layer formed on the diffusion barrier coating. The diffusion barrier layer may include iridium. | 05-15-2014 |
20140074410 | DETECTION AND MEASUREMENT OF DEFECT SIZE AND SHAPE USING ULTRASONIC FOURIER-TRANSFORMED WAVEFORMS - A system may include a data analysis device that is configured to receive from an ultrasonic waveform detector ultrasonic waveform data representative of an ultrasonic waveform that propagated through a sample and resonated within a defect within the sample. The data analysis device may be further configured to select a portion of the ultrasonic waveform data, apply a Fast Fourier Transform to the portion of the ultrasonic waveform data to transform the portion from a time domain to a frequency domain, identify a characteristic frequency of the portion in the frequency domain, and determine a characteristic of the defect based on the characteristic frequency of the portion. In some examples, the characteristic of the defect may be at least one of an approximate size or an approximate shape of the defect. | 03-13-2014 |
20140072816 | BOND LAYERS FOR CERAMIC OR CERAMIC MATRIX COMPOSITE SUBSTRATES - A bond layer may include a composition that may be stable at temperatures above about 1410° C. An article may include a substrate, a bond layer formed on the substrate, and an overlayer formed over the bond layer. In some examples, the bond layer may include a substantially homogeneous mixture of Si and at least one of SiO | 03-13-2014 |
20130253858 | ULTRASONIC MEASUREMENT AND DETERMINATION OF CRYSTALLOGRAPHIC TEXTURE WITH RESPECT TO POSITION - A technique and device ( | 09-26-2013 |
20130224457 | THERMAL BARRIER COATINGS INCLUDING CMAS-RESISTANT THERMAL BARRIER COATING LAYERS - An article may include a superalloy substrate and a calcia-magnesia-alumina-silicate (CMAS)-resistant thermal barrier coating (TBC) layer overlying the superalloy substrate. In some embodiments, the CMAS-resistant TBC layer includes between about 50 wt. % and about 90 wt. % of a TBC composition and between about 10 wt. % and about 50 wt. % of a CMAS-resistant composition. In some examples, the TBC composition includes at least one of yttria-stabilized zirconia, yttria-stabilized hafnia, zirconia stabilized with at least three rare earth oxides, or hafnia stabilized with at least three rare earth oxides. In some examples, the CMAS-resistant composition includes alumina, silica, and an oxide of at least one of Sc, Y, La, Ce, Pr, Nd, Pm, Sm, Eu, Gd, Yb, Dy, Ho, Er, Tm, Tb, or Lu. | 08-29-2013 |
20130220488 | METHOD FOR CARBURIZING STEEL COMPONENTS - A carburizing process for increasing the hardness of a case region of a steel component. In one form the application includes plating the outer surface of a stainless steel component with nickel prior to carburizing. One component includes a stainless steel object having a hardened case substantially free of continuous phase grain boundary carbides. | 08-29-2013 |
20130189531 | MULTILAYER CMAS-RESISTANT BARRIER COATINGS - An article comprising a substrate, a calcia-magnesia-alumina-silicate-resistant (CMAS-resistant) layer or a plurality thereof, including a rare earth oxide and alumina formed over the substrate, and a barrier coating layer formed on the CMAS-resistant layer. The barrier coating layer or a plurality thereof, comprising a thermal barrier coating composition or an environmental barrier coating composition. | 07-25-2013 |
20130154161 | METHOD AND APPARATUS ASSOCIATED WITH ANISOTROPIC SHRINK IN SINTERED CERAMIC ITEMS - A manufacturing method for producing ceramic item from a photocurable ceramic filled material by stereolithography. The method compensates for the anisotropic shrinkage of the item during firing to produce a dimensionally accurate item. | 06-20-2013 |
20130136915 | DURABLE ENVIRONMENTAL BARRIER COATINGS FOR CERAMIC SUBSTRATES - An article includes a substrate and an environmental barrier coating overlying the substrate. The environmental barrier coating includes a first dense layer, an intermediate layer overlying the first dense layer, and a second dense layer overlying the intermediate layer. The first dense layer includes at least one of a first rare earth silicate or barium strontium aluminosilicate and the second dense layer includes at least one of a second rare earth silicate or barium strontium aluminosilicate. Additionally, the intermediate layer includes at least one of a porous microstructure, a lamellar microstructure, or an absorptive material. | 05-30-2013 |
20130122259 | FEATURES FOR MITIGATING THERMAL OR MECHANICAL STRESS ON AN ENVIRONMENTAL BARRIER COATING - An article may include a substrate comprising a matrix material and a reinforcement material, a layer formed on the substrate, an array of features formed on the layer, and a coating formed on the layer and the array of features. The article may have improved thermal and/or mechanical stress tolerance compared to an article not including the array of features formed on the layer. | 05-16-2013 |
20130108421 | ABRADABLE CERAMIC COATINGS AND COATING SYSTEMS | 05-02-2013 |
20130062323 | TECHNIQUES FOR REMOVING A CONTAMINANT LAYER FROM A THERMAL BARRIER COATING AND ESTIMATING REMAINING LIFE OF THE COATING - Systems and techniques are disclosed for removing contaminants from a surface of a thermal barrier coating (TBC) and, optionally, estimating the remaining lifetime of the TBC. Laser induced breakdown spectroscopy (LIBS) is one method that may be used to remove contaminants from a surface the TBC prior to performing photo luminescence piezo spectroscopy (PLPS) or another spectroscopic technique on a thermally grown oxide (TGO). LIBS may facilitate monitoring substantially in real-time the chemical composition of the material removed. LIBS may be used to remove substantially only the contaminants with minimal effects on the underlying TBC. One technique for determining when to stop removal of material from the TBC is cross-correlation between a spectrum collected from the ablated material and a reference spectrum collected from a reference substrate. In some embodiments, the same system may be used to perform LIBS to remove impurities and PLPS to measure stress in the TGO. | 03-14-2013 |
20130048206 | AIRFOIL ASSEMBLY AND METHOD OF FORMING SAME - An airfoil or vane for a combustive power plant includes an inner core formed from a first composite material having discontinuous fibers. An outer sleeve is formed from a second composite material having continuous fibers. The first composite material is different from the second composite material. The outer sleeve generally surrounds and is bonded or otherwise connected to the inner core. A method of fabrication includes injecting or otherwise introducing thermoplastic fiber composite material including chopped or otherwise discontinuous fibers into a mold to form the core and platforms of an airfoil assembly. The injected thermoplastic fiber composite material is then cured in the mold. The cured thermoplastic fiber composite material is then removed from the mold. A layup including one or more surface plies of a thermoset continuous fiber composite material is then applied to the core material. The surface plies are then compressed and cured in a mold. | 02-28-2013 |
20120262160 | ASYMMETRIC VARIABLE RELUCTANCE (VR) TARGET FOR MULTI-DIMENSIONAL MONITORING - A system is provided for dynamically determining an axial position of a rotating member. The system includes a target component on a circumferential periphery of the rotating member, the target component having a longitudinally asymmetric shape. The system further includes a sensor assembly fixedly positioned relative to the target component. The sensor assembly detects and outputs a plurality of signals having different positive pulse widths, as the target component moves axially past the sensor. The system further includes a circuit coupled to the sensor assembly and receiving the plurality of signals. The circuit determines an axial position of the target component for each of the plurality of signals based on a comparison of the different positive pulse widths. | 10-18-2012 |
20120192567 | GAS TURBINE ENGINE FLANGE ASSEMBLY INCLUDING FLOW CIRCUIT - One embodiment is a unique apparatus having a gas turbine engine flange assembly. Another embodiment is a unique system having a gas turbine engine flange assembly. Still other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for gas turbine engine flange assemblies. Further embodiments, forms, objects, features, advantages, aspects, embodiments and benefits shall become apparent from the following descriptions, drawings, and claims. | 08-02-2012 |
20120128879 | ABRADABLE LAYER INCLUDING A RARE EARTH SILICATE - An abradable coating may include a rare earth silicate. The abradable coating may be deposited over a substrate, an environmental barrier coating, or a thermal barrier coating. The abradable coating may be deposited on a gas turbine blade track or a gas turbine blade shroud to form a seal between the gas turbine blade track or gas turbine blade shroud and a gas turbine blade. The abradable coating may also include a plurality of layers, such as alternating first and second layers including, respectively, a rare earth silicate and stabilized zirconia or stabilized hafnia. | 05-24-2012 |
20110197999 | METHODS FOR MAKING HIGH-TEMPERATURE COATINGS HAVING PT METAL MODIFIED GAMMA-NI +GAMMA'-NI3AL ALLOY COMPOSITIONS AND A REACTIVE ELEMENT - A method for making an oxidation resistant article, including (a) depositing a layer of a Pt group metal on a substrate to form a platinized substrate; and (b) depositing on the platinized substrate layer of Pt group metal a layer of a reactive element selected from the group consisting of Hf, Y, La, Ce and Zr and combinations thereof to form a surface modified region thereon, wherein the surface modified region includes the Pt-group metal, Ni, Al and the reactive element in relative concentration to provide a γ-Ni+γ-Ni3Al phase constitution. | 08-18-2011 |
20110097538 | Substrate Features for Mitigating Stress - An article may include an array of features formed in a substrate and may be coated by a thermal barrier coating (TBC). The array of features may mitigate thermal stress experienced by the coated article. In particular, the array of features may reduce or limit crack propagation at or above the interface of a thermally insulative layer and a bond coat in the TBC. In some embodiments, the array may be formed proximate to and substantially aligned with cooling holes formed in the substrate. In other embodiments, an article may include a first array of features formed in a first location of a substrate and a second array of features formed in a second location of a substrate. The first and second locations may be determined or selected based on a prediction of thermal stresses that the substrate will experience at the first and second locations during use. | 04-28-2011 |
20110033630 | TECHNIQUES FOR DEPOSITING COATING ON CERAMIC SUBSTRATE - A method of coating a substrate, the method including depositing mullite on the substrate during a first time period via thermal spraying to form a first layer, the mullite comprising mullite powder formed via at least one of a fused plus crush or sinter plus crush process; and depositing a second material on the first layer to form a second layer, wherein the substrate is at a temperature less than approximately 50 degrees Celsius at approximately a beginning of the first time period. In some embodiments, the method may further include depositing silicon to form a silicon bond layer between the substrate and mullite layer. | 02-10-2011 |
20110025157 | SYSTEM OF ELECTRICAL GENERATION FOR COUNTER-ROTATING OPEN-ROTOR BLADE DEVICE - A counter-rotating open-rotor blade aircraft propulsion system includes a structure supporting a plurality of blades. A rotor is drivingly coupled to the structure supporting the plurality of blades. The rotor includes a rotating coil disposed in the structure supporting the plurality of blades. A rotating magnetic field source includes two Halbach permanent magnet arrays. | 02-03-2011 |
20110018273 | STARTER/GENERATOR INTEGRATED INTO COMPRESSOR OF TURBINE ENGINE - A turbine engine compressor has a rotor including rotating compressor discs. Magnets are positioned on the rotating compressor discs. Electrical coils are positioned in a stationary guide vane internal ring so as to create an electric machine providing starting torque to a rotor, and/or generating electrical energy once the rotor is rotating. | 01-27-2011 |
20110014060 | Substrate Features for Mitigating Stress - An article may include an array of features formed in a substrate and may be coated with a coating layer. The array of features may mitigate stress experienced by the coated article. In particular, the array of features may reduce or limit crack propagation at the interface between the substrate and the coating layer. In some examples, the article is an airfoil that includes a tip that defines an edge. An array of features is formed on the surface of the tip, where the array of features is proximate to the edge, and the array of features does not intersect the edge. The airfoil includes a coating layer formed on the surface of the tip and the array of features. | 01-20-2011 |
20100287905 | TURBINE ENGINE THRUST SCHEDULING - This invention relates generally to gas turbine engine thrust scheduling, and more particularly to systems and methods for smoothing thrust inputs to gas turbine engines. In one embodiment, a method for operating a gas turbine engine comprises, upon disengagement of an auto-throttle system, determining a first trim setting corresponding to a TLA setting, determining a second trim setting where the second trim setting reduces to zero during successive manual throttle lever movements, determining a third trim setting comprising a combination of the first trim setting and the second trim setting, and applying the third trim setting to the TLA setting to smoothly transition from auto-throttle to manual operation of the engine while maintaining engine thrust. | 11-18-2010 |
20100255260 | SLURRY-BASED COATING TECHNIQUES FOR SMOOTHING SURFACE IMPERFECTIONS - An article may include a substrate defining a surface imperfection and a coating deposited over the substrate. The coating does not substantially reproduce the surface imperfection, and the coating comprises mullite and at least one rare earth silicate, rare earth oxide, alumina, boron oxide, alkali metal oxide, alkali earth metal oxide, silicon, barium strontium aluminosilicate, barium aluminosilicate, strontium aluminosilicate, calcium aluminosilicate, magnesium aluminosilicate, or lithium aluminosilicate. In some examples, the coating may be a first coating deposited from a slurry over the substrate, and a second coating may be deposited over the first coating. In other examples, a first coating that substantially reproduces the surface imperfection may be deposited over the substrate, and the coating that does not substantially reproduce the surface imperfection may be deposited over the first coating. | 10-07-2010 |
20100159136 | STATIC CHEMICAL VAPOR DEPOSITION OF y-Ni + y'-Ni3AI COATINGS - A static chemical vapor deposition (CVD) process may be used to deposit a coating including a γ-Ni+γ′-Ni | 06-24-2010 |
20100136349 | MULTILAYER THERMAL BARRIER COATINGS - A multilayer thermal barrier coating (TBC) may include a plurality of layers selected to provide properties to the multilayer TBC. For example, a multilayer TBC may include a first layer deposited over a substrate, a second layer deposited over the first layer and a third layer deposited over the second layer. The first layer may be selected to provide thermal cycling resistance, the second layer may be selected to provide low thermal conductivity and the third layer may be selected to provide at least one of erosion resistance and CMAS degradation resistance. The multilayer TBC may also include two layers, or more than three layers. | 06-03-2010 |
20100129673 | REINFORCED OXIDE COATINGS - A reinforced coating may include an oxide matrix and a reinforcement. In some embodiments, the reinforcement may include at least one of SiC and Si | 05-27-2010 |
20100129636 | ABRADABLE LAYER INCLUDING A RARE EARTH SILICATE - An abradable coating may include a rare earth silicate. The abradable coating may be deposited over a substrate, an environmental barrier coating, or a thermal barrier coating. The abradable coating may be deposited on a gas turbine blade track or a gas turbine blade shroud to form a seal between the gas turbine blade track or gas turbine blade shroud and a gas turbine blade. The abradable coating may also include a plurality of layers, such as alternating first and second layers including, respectively, a rare earth silicate and stabilized zirconia or stabilized hafnia. | 05-27-2010 |
20100127496 | GAS TURBINE ENGINE WITH INTEGRATED ELECTRIC STARTER/GENERATOR - An electrical machine is embedded into the compressor assembly of a gas turbine engine. An electrical system interface module distributes electrical current to and from the embedded electrical machine for starting the gas turbine engine and for operating accessory components. Accordingly, the gas turbine engine and accessory components can be started and operated without a power-takeoff shaftline and without an external accessory gearbox. | 05-27-2010 |
20100057957 | RECONFIGURABLE FADEC FOR GAS TURBINE ENGINE - A reconfigurable FADEC includes a reconfigurable CPU configured for performing digital computing functions. A reconfigurable MSPD communicates with the CPU and is configured for performing analog I/O functions. A data bus is coupled to the CPU and the MSPD. The data bus is configured for connecting the CPU and the MSPD to an external connector. | 03-04-2010 |
20100024427 | PRECISION COUNTER-SWIRL COMBUSTOR - A precision counter-swirl combustor that includes an annular combustor having a forward end, an aft end opposite the forward end, and an interior. The aft end being proximal to a gas turbine. The combustor further includes a fuel inlet and swirler operatively connected to the forward end and at least one air inlet. The air inlet is equipped with a chute that extends into the interior of said combustor. The combustor is secured to a fixed structure proximate the forward end of the combustor. | 02-04-2010 |
20090289232 | GAS TURBINE ENGINE AND METHOD INCLUDING COMPOSITE STRUCTURES WITH EMBEDDED INTEGRAL ELECRICALLY CONDUCTIVE PATHS - A gas turbine engine and method of fabrication includes a gas turbine engine with a structure having movable portions and static portions. At least a portion of the structure includes a composite material having an electrically conductive path formed from carbon nanotubes configured for conducting electrical signals therealong. | 11-26-2009 |