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Gas Turbine patents



      
           
This page is updated frequently with new Gas Turbine-related patent applications. Subscribe to the Gas Turbine RSS feed to automatically get the update: related Gas RSS feeds. RSS updates for this page: Gas Turbine RSS RSS


Contoured flowpath surface

United Technologies

Contoured flowpath surface

Gas turbine combustor and gas turbine

Mitsubishi Heavy Industries

Gas turbine combustor and gas turbine

Gas turbine combustor and gas turbine

Solar Turbines

Turbine blade platform seal assembly validation


Date/App# patent app List of recent Gas Turbine-related patents
07/23/15
20150204760 
 Method for monitoring the operation of a gas turbine patent thumbnailnew patent Method for monitoring the operation of a gas turbine
A method for monitoring the operation of a gas turbine is provided, in which component vibrations are detected during the operation of the gas turbine by an acceleration sensor arranged on the component, a plurality of signal sections being determined by a plurality of frequency bands fb from the signal forwarded and processed by the acceleration sensor. To avoid an unnecessary shutdown of the gas turbine to perform an inspection which subsequently proves unnecessary, thereby increasing the availability of the gas turbine, a total vibration period is determined by adding together the vibration periods of signal sections during which the amplitudes of the signal sections concerned are greater than a frequency band-specific threshold..
Siemens Aktiengesellschaft


07/23/15
20150204543 
 Gas turbine combustor and gas turbine patent thumbnailnew patent Gas turbine combustor and gas turbine
A gas turbine combustor is disposed in a casing interior space of a gas turbine. A combustor basket of the combustor is formed into a cylindrical shape by abutting ends of a curved panel member and welding the ends together along a welding line 16.
Mitsubishi Heavy Industries, Ltd.


07/23/15
20150204439 
 Variable vane actuating system patent thumbnailnew patent Variable vane actuating system
A variable vane assembly for a gas turbine engine having an actuating system including a rotatable face gear and a respective pinion engaged to and extending transversely from the end of each of the moveable vanes. The teeth of each pinion define land surfaces angled with respect to adjacent ones of the land surfaces of the teeth of the face gear meshed therewith.
Pratt & Whitney Canada Corp.


07/23/15
20150204347 
 Fan blades with abrasive tips patent thumbnailnew patent Fan blades with abrasive tips
A fan blade for a gas turbine engine is disclosed. The disclosed fan blade includes an airfoil having a leading edge, a trailing edge, a convex side, a concave side and a distal tip.
United Technologies Corporation


07/23/15
20150204247 
 Method of operating a gas turbine assembly and the gas turbine assembly patent thumbnailnew patent Method of operating a gas turbine assembly and the gas turbine assembly
The invention relates to a method of operating a gas turbine assembly, which includes a compressor, a combustor and a gas turbine. The method includes operating the gas turbine assembly at a partial load with respect to a base load of the gas turbine assembly; bypassing a portion of blow-off air from the compressor; and introducing the portion of blow-off air into an exhaust gas duct after the gas turbine.
Alstom Technology Ltd.


07/23/15
20150204245 
 Turbine blade platform seal assembly validation patent thumbnailnew patent Turbine blade platform seal assembly validation
A platform seal assembly for a gas turbine engine with a turbine disk and a plurality of turbine blades is disclosed. The platform seal assembly includes a platform seal and a validation tab.
Solar Turbines Incorporated


07/23/15
20150204244 
 Selectively deoxygenated stored fuel system patent thumbnailnew patent Selectively deoxygenated stored fuel system
A gas turbine engine includes a multi-stage fuel injection system including at least a first fuel injection stage and a second fuel injection stage, a first fuel reservoir fluidly connected to the first fuel injection stage and fluidly connected to a selective valve, and a second fuel reservoir fluidly connected to the selective valve. The selective valve connects one of the first fuel reservoir and the second fuel reservoir to the second fuel injection stage..
United Technologies Corporation


07/23/15
20150204243 
 Structural support bracket for gas flow path patent thumbnailnew patent Structural support bracket for gas flow path
A structural support system is provided in a can annular gas turbine engine having an arrangement including a plurality of integrated exit pieces (ieps) forming an annular chamber for delivering gases from a plurality of combustors to a first row of turbine blades. A bracket structure is connected between an iep and an inner support structure on the engine.
Siemens Energy, Inc.


07/23/15
20150204242 
 Fastener patent thumbnailnew patent Fastener
The present invention provides a fastener for securing two pipe adapters within a casing such as a gas turbine casing. The fastener comprises a fastener body having a central bore for receiving the pipe adapters and having a first engagement portion, e.g.
Rolls-royce Plc


07/23/15
20150204241 
 Method and  operating a gas turbine power plant at low load conditions with stack compliant emissions levels patent thumbnailnew patent Method and operating a gas turbine power plant at low load conditions with stack compliant emissions levels
An apparatus for a gas turbine power plant that uniquely configures emission control equipment such that the plant can extend the emissions compliant operational range, the apparatus including a plurality of oxidation (co) catalysts arranged in series.. .
Mitsubishi Hitachi Power Systems Americas, Inc.


07/23/15
20150204239 
new patent

System and controlling the combustion process in a gas turbine operating with exhaust gas recirculation


A system includes a fuel control system configured to control a fuel flow to one or more combustors and an oxidant control system configured to control an oxidant flow to each combustor of the one or more combustors, wherein the oxidant flow is configured to at least partially react with the fuel flow within the one or more combustors to form an exhaust gas flow. The system also includes an exhaust gas system configured to direct a recirculation flow of the exhaust gas flow to each combustor of the one or more combustors; and a controller coupled to the fuel control system, the oxidant control system, and the exhaust gas system.
Exxonmobil Upstream Research Company


07/23/15
20150204238 
new patent

Low noise turbine for geared turbofan engine


A gas turbine engine includes a fan, a turbine having a fan drive rotor, and a speed reduction device effecting a reduction in the speed of the fan relative to an input speed from the fan drive rotor. The fan drive rotor has a number of turbine blades in at least one of a plurality of rows of the fan drive rotor, and the turbine blades operating at least some of the time at a rotational speed, and the number of turbine blades in the at least one row and the rotational speed being such that the following formula holds true for the at least one row of the fan drive turbine (the number of blades×the rotational speed)/(60 seconds/minute)>4000 hz.
Mtu Aero Engines Ag


07/23/15
20150204214 
new patent

Method and operating a gas turbine power plant at low load conditions with stack compliant emissions levels


An apparatus for a gas turbine power plant that uniquely configures emission control equipment such that the plant can extend the emissions compliant operational range, the apparatus including a plurality of oxidation (co) catalysts arranged in series, optimized scr for high no2 reduction, control valves with added capabilities for low turndown and other characteristics.. .
Mitsubishi Hitachi Power Systems Americas, Inc.


07/23/15
20150204212 
new patent

High durability turbine exhaust case


A turbine exhaust case has an outer housing to be secured within a gas turbine engine and a central hub. Struts extend between the outer housing and the central hub.
Gkn Aerospace Sweden Ab


07/23/15
20150204210 
new patent

Method of inspecting the fan track liner of a gas turbine engine


A method of inspecting the fan track liner of a gas turbine engine of a type having a rotatable propulsive fan circumscribed by a fan track liner and having a plurality of fan blades extending radially outwardly from a central hub. The method comprises the steps of: affixing at least part of an inspecting device to the fan so as to be directed towards the fan track liner; and rotating the fan within the fan track liner to move said at least part of the inspecting device circumferentially relative to at least a region of the fan track liner to thereby scan said region of the fan track liner with said at least part of the inspecting device..
Rolls-royce Plc


07/23/15
20150204201 
new patent

Contoured flowpath surface


A spacer assembly for a rotor assembly of a gas turbine engine includes an endwall segment having a non-axisymmetric flowpath surface, a first depression and a second depression. A perimeter of the flowpath surface includes a forward edge, an aft edge, a suction side edge and a pressure side edge.
United Technologies Corporation


07/23/15
20150204196 
new patent

Gas turbine


The object of the invention is to suppress development of a secondary current whirl in the vicinity of a rotor blade front edge of a gas turbine even when a cooling refrigerant is mixed in from the front edge of an end wall section of the rotor blade. In a gas turbine rotor blade 4 including a wing shape section 12 formed of a negative pressure surface 12d extending from a front edge 12a to a rear edge 12b, a pressure surface 12c opposing the negative pressure surface 12d and extending from the front edge 12a to the rear edge 12b, and a tip surface 13 surrounded by the top end of the negative pressure surface 12d and the top end of the pressure surface 12c, and an end wall section 10 connected to the bottom end of the negative pressure surface 12d and the bottom end of the pressure surface 12c, the rotor blade has a convex shape in positions constituting the negative pressure surface 12d side and the front edge 12a side of the end wall section 10, and the rotor blade has a concave shape in positions constituting the pressure surface 12c side and the front edge 12a side of the end wall section 10..
Mitsubishi Hitachi Power Systems, Ltd.


07/23/15
20150203209 
new patent

Gas turbine engine configuration interface


A gas turbine engine is disclosed which is capable of being reconfigured for one operating mode to another. A display is provided that permits a pilot or other operator to select between engine modes.
Rolls-royce North American Technologies, Inc.


07/23/15
20150202707 
new patent

Attachment of structures having different physical characteristics


Methods of bonding first structures to second structures are disclosed wherein the first and second structures are fabricated materials having different physical characteristics. For example, the first structure may be a composite fan blade and the second structure may be a composite or metallic rotor, both for use in gas turbine engines.
United Technologies Corporation


07/23/15
20150202702 
new patent

Gas turbine engine cast structure finishing


A method of finishing a cast structure includes providing a cast exterior surface with an undesired cast feature and electrochemically machining the undesired cast feature to provide a finished contour.. .
United Technologies Corporation


07/16/15
20150198335 

Liner, flow sleeve and gas turbine combustor each having cooling sleeve


A gas turbine combustor includes a liner and a transmission piece. Fuel injected in the liner from a fuel nozzle of a gas turbine mixes with compressed air.
Doosan Heavy Industries & Construction Co., Ltd.


07/16/15
20150198334 

Sequential combustion arrangement with dilution gas


The invention refers to a sequential combustor arrangement including a first combustor with a first burner for admitting a first fuel into a combustor inlet gas during operation and a first combustion chamber for burning the first fuel, a dilution gas admixer for admixing a dilution gas to the first combustor combustion products leaving the first combustion chamber, and a second burner for admixing a second fuel and a second combustion chamber. To assure good mixing over a wide operating range, the ratio of the pressure loss of the first combustor to the pressure loss of the dilution gas admixer is in the range of 1 to 6.
Alstom Technology Ltd


07/16/15
20150198333 

Fuel injector with a diffusing main gas passage


A fuel injector for a combustor of a gas turbine engine is disclosed. The fuel injector includes a gas gallery and a gas passage.
Solar Turbines Incorporated


07/16/15
20150198116 

Variable area exhaust mixer for a gas turbine engine


A variable area exhaust mixer is provided for a gas turbine engine. The variable area exhaust mixer includes an outer wall with a multiple of doors.
United Technologies Corporation


07/16/15
20150198097 

Systems and methods for managing a combustor


Certain embodiments herein relate to systems and methods for managing a combustor of a gas turbine engine. In one embodiment, a system can include at least one memory configured to store computer-executable instructions and at least one controller configured to access the at least one memory and execute the computer-executable instructions.
General Electric Company


07/16/15
20150198092 

Dual function air diverter and variable area fan nozzle


A modulating fan air diverter and annular air-oil cooler for a gas turbine engine located in the inner fixed structure adjacent to the core cowl is provided. The fan air diverter modulates between an open position, corresponding to maximum fan nozzle area and airflow through the air-oil cooler, and a closed position, corresponding to minimum fan nozzle area and airflow through the air-oil cooler.
United Technologies Corporation


07/16/15
20150198091 

Electric probe assembly, gas turbine engine having same and cooling same


A gas turbine engine comprises a hot section module which includes at least one electric probe assembly surrounded by an immediate environment having a local ambient temperature. The at least one electric probe assembly includes an electric probe having a probe body, and a conduit surrounding at least a portion of the probe body.
Pratt & Whitney Canada Corp.


07/16/15
20150198089 

Gas turbine oxidant separation system


In one embodiment, a system includes a gas turbine system, having: a turbine driven by combustion products produced by a turbine combustion system; and a separation unit positioned between turbine stages of the turbine, wherein the separation unit separates oxygen out of the combustion products. The separation unit may include an ion transport membrane..
Exxonmobil Upstream Research Company


07/16/15
20150198088 

Power generation system for using syngas generated in gasifier to produce electricity


A power generation system including a gasifier for receiving and converting coal-water slurry to a fuel stream, and a quench device for cooling the fuel stream to generate a cooled down fuel stream. The quench device includes a water quench ring, which is able to spray water to cool the fuel stream passing therethrough.
General Electric Company


07/16/15
20150198063 

Cooled stator heat shield


The present invention provides a stator heat shield for a gas turbine. The gas turbine includes a rotor defining an axis of rotation.
Alstom Technology Ltd


07/16/15
20150198062 

Turbine components with bi-material adaptive cooling pathways


The present application thus provides a turbine component for use in a hot gas path of a gas turbine engine. The turbine component may include an outer surface, an internal cooling circuit, an adaptive cooling pathway in communication with the internal cooling circuit and extending through the outer surface, and a cooling plug having two or more materials positioned within the adaptive cooling pathway..
General Electric Company


07/16/15
20150198059 

Gas turbine manual cleaning and passivation


A gas turbine engine may be manually cleaned by removing a compressor casing and a turbine casing from the gas turbine engine, cleaning stator vanes of the gas turbine engine, and applying an organic acid solution to metallic surfaces of the gas turbine engine. The organic acid solution may be rinsed from the gas turbine engine and an anticorrosive solution may be applied to the metallic surfaces of the gas turbine engine..
General Electric Company


07/16/15
20150198056 

Abradable seal having nanolayer material


A gas turbine engine includes a plurality of circumferentially-spaced blades. The blades have a polymeric coating thereon.
United Technologies Corporation


07/16/15
20150198055 

Gas turbine including sealing band and anti-rotation device


A turbine is provided comprising a plurality of stages, each stage comprising a rotatable disk and blades carried thereby, at least one pair of adjacent rotatable disks defining an annular gap therebetween and having respective opposing sealing band receiving slots aligned with the annular gap a sealing band is located in the opposing receiving slots to seal the annular gap disk engagement structure is defined in the pair of adjacent rotatable disks. A clip member is coupled to the sealing band and engaged with the pair of adjacent rotatable disks through the disk engagement structure the clip member may have an aperture extending only partially through the clip member for alignment with a hole in the sealing band for engagement with a tool to improve weld geometry, the clip member may have angled surfaces and notched areas, and the sealing band may have chamfered edges..
Siemens Energy, Inc.


07/16/15
20150198054 

Assembly for directing combustion gas


An arrangement is provided for delivering gases from a plurality of combustors of a can-annular gas turbine combustion engine to a first row of turbine blades including a first row of turbine blades. The arrangement includes a gas path cylinder, a cone and an integrated exit piece (iep) for each combustor.
Siemens Energy, Inc.


07/16/15
20150198053 

Gas turbine engine with exit flow discourager


A turbine stage for a gas turbine engine is disclosed. The turbine stage includes a turbine disk and a turbine diaphragm, forming a cavity there between.
Solar Turbines Incorporated


07/16/15
20150198050 

Internal cooling system with corrugated insert forming nearwall cooling channels for airfoil usable in a gas turbine engine


An airfoil for a gas turbine engine in which the airfoil includes an internal cooling system formed from one or more midchord cooling channels with a corrugated insert positioned therein and creating nearwall leading edge, pressure side and suction side nearwall cooling channels. The corrugated insert may be formed from a wall that oscillates in a repeating pattern between peaks and valleys, such that the peaks are closer to an inner surface of the outer wall forming the generally elongated hollow airfoil the corrugated insert may work in concert with the rows of partition walls to create periodic impingement on the inner surface of the outer wall such cooling system provides adequate cooling for use in environments in which few, if any, cooling holes are desired, such as in crude oil engine applications.
Siemens Energy, Inc.


07/16/15
20150198047 

Mistuned airfoil assemblies


A mistuned airfoil assembly for a gas turbine engine is disclosed. The mistuned airfoil assembly may comprise a hub and airfoils extending radially from the hub.
United Technologies Corporation


07/16/15
20150198044 

Gas turbine having damping clamp


An exemplary gas turbine includes a rotor unit, a tie-bolt, a cooling air pipe, and a clamping member. The rotor unit includes rotor blades and rotor disks.
Doosan Heavy Industries & Construction Co., Ltd.


07/16/15
20150197700 

Nano-dispersions of carbonaceous material in water as the basis of fuel related technologies and methods of making same


Colloidal carbonaceous material-in-water slurries having nano-particles of carbonaceous material creating a pseudo-fluid. The colloidal carbonaceous material-in-water slurry generally includes from about fifty to about seventy two weight percent of carbonaceous material, with about 20 to about 80 percent of the carbonaceous material having a particle size of about one micron or less with a mode particle size of about 250 nanometers.
Nano Dispersions Technology, Inc.


07/16/15
20150197456 

Protective coating systems for gas turbine engine applications and methods for fabricating the same


Protective coating systems for gas turbine engine applications and methods for fabricating such protective coating systems are provided. An exemplary protective coating system includes a substrate formed of a ceramic matrix composite material, a first coating layer formed directly on to the substrate and comprising an oxygen barrier material, a compliance material, or a bonding material and a second coating layer formed directly on to the first coating layer and comprising a thermal barrier material.
Honeywell International Inc.


07/16/15
20150196868 

Gas turbine inlet gas phase contaminant removal


A sorption arrangement for a gas turbine includes a sorbent-laden media. The sorbent-laden media is positioned within an inlet system for the gas turbine.
Bha Altair, Llc


07/09/15
20150192912 

Method and system for combustion mode transfer for a gas turbine engine


A method and system for transferring between combustion modes in a gas turbine engine is provided. A processor generates data representative of an initial set of splits for providing at least one of fuel and air to at least one combustor in the gas turbine engine.
General Electric Company


07/09/15
20150192300 

Light weight swirler for gas turbine engine combustor and a manufacturing


A swirler body for a combustor of a gas turbine engine includes an annular mount face which defines at least one pocket and a method of manufacturing.. .
United Technologies Corporation


07/09/15
20150192299 

Compensating for thermal expansion via controlled tube buckling


One embodiment includes a fuel injector for a gas turbine engine. The fuel injector has an inlet fitting for receiving fuel.
Delavan Inc.


07/09/15
20150192298 

Gas turbine engine with improved fuel efficiency


A turbofan engine includes a fan driven by a low pressure turbine through a gear reduction. The gear reduction has a gear ratio of greater than or equal to about 2.4.
United Technologies Corporation


07/09/15
20150192165 

Systems and methods for centering bearing compartments


Systems and methods are disclosed herein for dressing centering a bearing compartment in a gas turbine engine. A nut may be inserted through an outer case of a gas turbine engine.
United Technologies Corporation


07/09/15
20150192074 

Fuel flow splitter and gas turbine fuel system health monitoring


A gas turbine health monitoring fuel system including a fuel splitter, a first and second fuel nozzle, a first and second fuel pump, and a common drive coupled to the first and second fuel pumps. The first and second fuel pumps are downstream from the fuel splitter.
Rolls-royce Corporation


07/09/15
20150192072 

Fluid transport system having divided transport tube


A fluid transport system for a gas turbine engine includes a plenum configured to provide a fluid, an airfoil having an internal cavity, and a transfer tube arranged to transfer the fluid between the plenum and the internal cavity of the airfoil. The transfer tube includes an inlet, an outlet, a cavity extending from the inlet to the outlet, and at least one partition wall dividing the cavity into multiple flow passages..
United Technologies Corporation


07/09/15
20150192071 

Geared turbofan gas turbine engine architecture


A gas turbine engine includes a combustor. A turbine section is in fluid communication with the combustor.
United Technologies Corporation


07/09/15
20150192070 

Geared turbofan gas turbine engine architecture


A gas turbine engine typically includes a fan section, a compressor section, a combustor section and a turbine section. A speed reduction device such as an epicyclical gear assembly may be utilized to drive the fan section such that the fan section may rotate at a speed different than the turbine section so as to increase the overall propulsive efficiency of the engine.
United Technologies Corporation


07/09/15
20150192069 

Recuperator for gas turbine engine


A recuperator inserted in the exhaust duct of a gas turbine engine includes a casing surrounding a core having spiral cross channels. Inlet and outlet openings are defined in the casing for the passage of hot exhaust gases through the exhaust channels in the core.
Pratt & Whitney Canada Corp.


07/09/15
20150192039 

Auxillary steam generation arrangement for a combined cycle power plant


A combined cycle plant (10) including: a gas turbine engine (12) having a compressor (14), a combustor and a gas turbine (16); a heat recovery steam generator (20) (hrsg) configured to receive exhaust from the gas turbine engine; a steam turbine (22, 24) configured to receive steam from the hrsg; a supplemental air arrangement (40) configured to generate supplemental heated air (42) when operating and to operate independent of the gas turbine engine; and a kettle boiler (26, 28) configured to use heat from the supplemental heated air to generate steam used in the steam turbine. .

07/09/15
20150192038 

Combined cycle plant injection water preheating arrangement


A combined cycle plant (10), including a heat recovery steam generator (hrsg) (36), a working fluid which is heated by the hrsg and effective to operate a steam turbine (38), and a blowdown heat transfer arrangement (90, 92, 94,102, 104) configured to capture heat present in blowdown water drawn from the working fluid and to transfer the heat to injection water (28), a gas turbine engine (16) having a compressor (18), a combustor (20), and a turbine (22), and a water injection arrangement (30) configured to inject the injection water into the combustor. .

07/09/15
20150192037 

Combined cycle plant fuel preheating arrangement


A combined cycle plant (10), including: a gas turbine engine (16) having a compressor (18), a combustor (20), and a gas turbine (22); and a heat recovery steam generator (hrsg) (36), a steam turbine (38), working fluid heated by the hrsg and effective to turn the steam turbine, and a blowdown heat transfer arrangement (90, 92, 94, 102, and 104) configured to capture heat present in blowdown water drawn from the working fluid and to transfer the heat to fuel (24) used in the combustor.. .

07/09/15
20150192036 

Preheating arrangement for a combined cycle plant


A power generation station (10), including: a combined cycle plant (12) having a gas turbine engine (20); a hrsg (30) configured to receive engine exhaust from the gas turbine engine and to generate steam, and a steam turbine (38, 40) configured to use the steam to develop mechanical energy; an auxiliary boiler (14) configured to generate heat used to create auxiliary steam for use in the combined cycle plant and to generate auxiliary boiler exhaust (52); and an auxiliary boiler exhaust heat transfer arrangement (16) configured to transfer heat present in the auxiliary boiler exhaust to the combined cycle plant.. .

07/09/15
20150192034 

Systems and methods for centering bearing compartments


Systems and methods are disclosed herein for dressing centering a bearing compartment in a gas turbine engine. A nut may be inserted through an outer case of a gas turbine engine.
United Technologies Corporation


07/09/15
20150192028 

Gas turbine


The aircraft-engine gas turbine includes an outer sealing ring for sealing an array of rotor blades that can be attached to a housing by a clamping means (80) in a friction fit, and a plurality of ring segments (20i, 20i+1), wherein a free axial path length (af) of a sealing ring segment counter to the direction of through-flow is at least as large as an axial engagement (a1) of a rotation locking member (10) of the outer sealing ring (af≧a1), which is free of form fit counter to the direction of through-flow, and/or an axial overhang (a2) of a radial mounting rail (23) of the outer sealing ring (af≧a2), and/or an axial offset (a3, a4) of a sealing fin (31, 41); and/or a quotient of a specific clearance sum of the outer sealing ring attached to the housing in a friction fit.. .
Mtu Aero Engines Ag


07/09/15
20150192026 

Gas turbine


The present invention relates to a gas turbine having a housing (1), an outer sealing ring (2) that can be fastened detachably to the housing, a clamping member (3) for clamping the outer sealing ring and the housing together radially, and a rotation locking member that has at least one housing groove (10) and a radial flange (20) of the outer sealing ring that can be locked against rotation in the housing groove in form-fitting manner with play (sa) in the axial and/or peripheral direction.. .
Mtu Aero Engines Ag


07/09/15
20150191252 

System and coordinated control of a power system


An integrated gas turbine engine, electrical power subsystem and thermal management subsystem for aerospace application includes a first motor/generator coupled to a low pressure (lp) shaft of the gas turbine engine, a second motor/generator coupled to a high pressure (hp) shaft of the gas turbine engine, and a system controller coupled to each of the gas turbine engine, a first motor generator and a second motor/generator, wherein the controller receives engine thrust demand and electrical power demand and is programmed to determine total system power demand and the amount of power sharing between the first motor/generator and the second motor/generator to meet thrust and electrical power demand.. .
Rolls-royce North American Technologies, Inc.


07/09/15
20150190890 

Systems, methods, and locating and drilling closed holes of a turbine component


Certain embodiments of the disclosure may include systems, methods, and apparatus for locating and drilling closed holes of a gas turbine component. According to an example embodiment, the method can include receiving position data associated with one or more holes in a gas turbine component; receiving predefined hole position data from manufacturing data associated with the gas turbine component; determining at least one missing hole, based at least in part on comparing the received position data to the predefined hole position data; and drilling at least one hole in the gas turbine component corresponding to the determined at least one missing hole..
General Electric Company


07/02/15
20150185111 

System and optimizing component life in a power system


An aircraft includes first and second gas turbine engines having a first component and a second component that is redundant with the first component, and an engine health monitoring system (ehms) coupled to the first and second gas turbine engines. The ehms is configured to calculate a remaining useful life (rul) of the first component and of the second component, calculate a rate-of-life consumption of the first component and of the second component, predict when failure of the first component and failure of the second component will occur based on the rul of each and based on the respective rate-of-life consumption of each, and provide instructions for altering operation of the aircraft that affects the rul of the first or second component..
Rolls-royce North American Technologies, Inc.


07/02/15
20150185089 

Acoustic transducer in system for gas temperature measurement in gas turbine engine


An apparatus for controlling operation of a gas turbine engine including at least one acoustic transmitter/receiver device located on a flow path boundary structure. The acoustic transmitter/receiver device includes an elongated sound passage defined by a surface of revolution having opposing first and second ends and a central axis extending between the first and second ends, an acoustic sound source located at the first end, and an acoustic receiver located within the sound passage between the first and second ends.
Siemens Energy, Inc.




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