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Matches 151 - 200 out of 8,405

Document Document Title
WO/2015/140350A1
The invention relates to a method for operating a gas turbine wherein a flowable fuel is generated by means of a gasifier device, this flowable fuel is supplied to a combustion chamber and flue gases produced by the combustion of this fu...  
WO/2015/136719A1
A gas turbine power generation system (1) has a dual-shaft gas turbine (3), an electric generator (4) mechanically connected to a low pressure turbine (304) of the dual-shaft gas turbine (3) and electrically connected to an electric powe...  
WO/2015/138030A2
A gas turbine engine according to an example of the present disclosure includes a drive turbine configured to drive a fan section, a speed change mechanism connected to the drive turbine and located aft of the drive turbine and aft of th...  
WO/2015/134009A1
A compressor exhaust flow static mixing system (10) formed from one or more radially inward extending static mixing arms (12) and one or more radially outward extending static mixing arms (14) that change the flow pattern of compressor e...  
WO/2015/132093A1
Cogeneration plant and method to operate a cogeneration plant The present invention is related to a cogeneration plant (1) comprising a gas turbine engine (10), a heat recovery steam generator (17) and a division module (21) forming a se...  
WO/2015/130386A3
The present disclosure relates generally to turbomachinery in which a rotating component is disposed adjacent a counter-rotating component in order to achieve a relative rotational velocity that is higher than would be achieved with a ro...  
WO/2015/130386A2
The present disclosure relates generally to turbomachinery in which a rotating component is disposed adjacent a counter-rotating component in order to achieve a relative rotational velocity that is higher than would be achieved with a ro...  
WO/2015/130898A1
The present disclosure relates to a power generation system and related methods that use supercritical fluids, whereby a portion of the supercritical fluid is recuperated.  
WO/2015/130363A3
In an embodiment, a method includes performing a turbine combustor diagnostic routine including operating a first turbine combustor of a plurality of turbine combustors at a substantially steady state of combustion; adjusting an operatio...  
WO/2015/124909A1
A fuel supply system for a gas turbine having at least one combustor (10), comprising at least one first heat exchanger (200A), receiving a fuel from a fuel source at a first temperature through a first fuel line (4) and provide the fuel...  
WO/2015/122799A1
A gas turbine installation includes an air compressor, a combustion chamber, a radial turbine having an impeller in the form of a disc with blades, and an electric generator located on the same shaft as the turbine. The air compressor is...  
WO/2015/118274A1
The invention relates to a system for the emergency starting of a turbomachine, characterized in that it comprises a spinner for driving the turbomachine, said spinner comprising a drum (2) secured to a rotation shaft (3), the axes of sy...  
WO/2015/119698A3
A gas turbine engine comprises a first turbine rotor positioned upstream of a second intermediate turbine rotor and a third turbine rotor positioned downstream of the first and second turbine rotors. A fan rotor and three compressor roto...  
WO/2015/117139A1
An assembly is provided for a turbine engine. This turbine engine assembly includes a combustor wall with a shell and a heat shield. The combustor wall defines a quench aperture therethrough. The combustor wall also defines a cavity betw...  
WO/2015/110296A1
The present invention relates to a combustor device (100) for a gas turbine (150). The combustor device (100) comprises an inner shell (110) which forms a combustion chamber (111) and an outer shell (120) surrounding the inner shell (110...  
WO/2015/112633A1
A gas turbine system (14) includes a fuel control system (264) configured to control a fuel flow to one or more combustors (160) and an oxidant control system (262) configured to control an oxidant flow to each combustor of the one or mo...  
WO/2015/112212A2
A gas turbine engine includes a fan section and a compressor section. The compressor section includes both a first compressor section and a second compressor section. A turbine section includes at least one turbine and driving the second...  
WO/2015/112231A2
A gas turbine engine comprises a fan rotor configured to be driven by a fan drive turbine through a first shaft and a gear reduction. The fan rotor is configured to deliver air into a bypass duct as bypass air and to deliver core air flo...  
WO/2015/112231A3
A gas turbine engine comprises a fan rotor configured to be driven by a fan drive turbine through a first shaft and a gear reduction. The fan rotor is configured to deliver air into a bypass duct as bypass air and to deliver core air flo...  
WO/2015/106981A1
The invention concerns a twin-shaft gas turbine (10) comprising a compressor (13), a high-pressure turbine (14), a low-pressure turbine (15), a first shaft (28) arranged in the compressor (13) and the high-pressure turbine (14) and a sec...  
WO/2015/106316A1
A gas turbine system with a turbine, a combustor for adding fuel to a working fluid and igniting the fuel to produce combustion gases that expand to drive the turbine and a steam ejector for introducing steam and compression to the worki...  
WO/2015/109038A1
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 c...  
WO/2015/105594A3
A gas turbine engine comprises a first turbine positioned upstream of a second intermediate turbine and a third turbine positioned downstream of the first and second turbines. A fan and three compressors, with an upstream one of the comp...  
WO/2015/105594A2
A gas turbine engine comprises a first turbine positioned upstream of a second intermediate turbine and a third turbine positioned downstream of the first and second turbines. A fan and three compressors, with an upstream one of the comp...  
WO/2015/102952A1
A turbine engine includes at least a compressor section and a turbine section, each having at least a first and second portion. A ratio of turbine section second portion stages to compressor section second portion stages is less than or ...  
WO/2015/102736A2
A combustor for a turbine engine includes an inner liner panel with a multiple of inner dilution passages. The multiple of dilution passages includes a repeating pattern of a first major inner air passage, a minor inner air passage, and ...  
WO/2015/102736A3
A combustor for a turbine engine includes an inner liner panel with a multiple of inner dilution passages. The multiple of dilution passages includes a repeating pattern of a first major inner air passage, a minor inner air passage, and ...  
WO/2015/092787A2
A compressor-less jet engine configured to generate thrust when the engine is at standstill.  
WO/2015/092088A1
The invention relates to a circular propulsion jet compressor-engine which, using a circular assembly of thrusters with spheroidal combustion chambers, generates propulsion tangential to the turning radius and the corresponding resulting...  
WO/2015/094430A1
A liner panel for use in a gas turbine engine. The liner panel has a hot side and a cold side. The liner panel includes a rail extending from the cold side and a multiple of studs extending from the cold side. At least one of the multipl...  
WO/2015/086951A1
The invention relates to a process for compressing a gaseous fluid comprising a step (a) of injecting refrigerant during which a refrigerant substance (3) is sprayed into the gaseous fluid (1) to be compressed, and also a compression ste...  
WO/2015/088859A2
A nickel-chromium (Ni-Cr) alloy and a method for electrodepositing the Ni-Cr alloy on a turbine engine component for dimensionally restoring the engine component are described. The engine component is restored by re-building wall thickne...  
WO/2015/088619A2
A turbofan engine includes a fan section including a fan blade having a leading edge and hub to tip ratio of less than about 0.34 and greater than about 0.020 measured at the leading edge and a speed change mechanism with gear ratio grea...  
WO/2015/086464A1
The off-shore gas turbine system comprises a floating structure with at least one deck (25) and a baseplate (31) mounted on the deck. The baseplate supports a gas turbine (1) having: a low pressure compressor, a high pressure compressor,...  
WO/2015/088830A1
Adapter plates for mounting accessories to a gearbox of a turbine engine are described herein. The adapter plates may be inverted to mount with various equipment, such as a variable frequency generator, oil pump, a fuel pump, a hydraulic...  
WO/2015/088606A2
A reverse-core turbofan engine including a propulsor section including a fan and a fan-tip turbine configured to deliver air to a core duct, including a first portion, disposed aft of the propulsor section, and direct air aft, toward an ...  
WO/2015/088606A3
A reverse-core turbofan engine including a propulsor section including a fan and a fan-tip turbine configured to deliver air to a core duct, including a first portion, disposed aft of the propulsor section, and direct air aft, toward an ...  
WO/2015/084747A1
A system includes a gas turbine engine configured to combust an oxidant and a fuel to generate an exhaust gas, a catalyst bed configured to treat a portion of the exhaust gas from the gas turbine engine to generate a treated exhaust gas,...  
WO/2015/084444A1
A wall assembly is provided for a gas turbine engine. This wall assembly includes a support shell with a contoured region; and a multiple of liner panels mounted to the support shell. At least one of the multiple of liner panels includes...  
WO/2015/080131A1
This combustion apparatus has a nozzle (35) in which a fuel injection port (41) for spraying fuel is formed on the center of the tip (35s) of said nozzle (35). Multiple water injection ports (42) are formed, at an interval in the circumf...  
WO/2015/079508A1
 Provided is a power generation system which adapts well to load fluctuations. A multi-shaft gas turbine power generation system provided with: a compressor (1) for compressing air to produce compressed air; a combustor (20) for produc...  
WO/2015/075346A1
The invention relates to a method for controlling a turbine engine (5) which includes a compressor (8), a combustion chamber (9), first and second turbines (10, 12), a first rotary shaft (11) rotatably secured to said compressor and to s...  
WO/2015/077755A1
An assembly for a turbine engine is provided. This turbine engine assembly includes a shell and a heat shield with a cooling cavity between the shell and the heat shield. The heat shield defines a plurality of cooling apertures and an in...  
WO/2015/077600A1
An assembly is provided for a turbine engine. This turbine engine assembly includes a body, a shell and a heat shield panel. The panel is attached to the shell with a tapered cooling cavity between the shell and the panel. The panel defi...  
WO/2015/075355A1
The invention relates to a turbofan engine comprising a fan (S) driven, via a fan shaft (3) supported by at least two first bearings (11, 12), by a turbine shaft (4) supported by at least one second bearing (10) comprising a stationary r...  
WO/2015/074052A1
A liner panel is provided for use in a combustor of a gas turbine engine. The liner panel includes a first liner panel side edge between a liner panel aft edge and a liner panel forward edge. The liner panel also includes a second liner ...  
WO/2015/069250A1
Systems and processes provide for a thermal process to transform sludge (and a variety of other natural waste materials) into electricity. Dewatered sludge and other materials containing a high amount of latent energy are dried into a po...  
WO/2015/069137A1
The mode of operation of the gas turbine plant provides supply of compressed air and steam methane-hydrogen mixture to a combustion chamber, cooling by means of evaporation or superheat of water steam directed to the gas turbine plant wh...  
WO/2015/067233A1
The invention relates to a method for using biomass even in high-temperature processes, something which has hardly been possible until now as a result of the fuel-related chlorides in flue gas and the problems of corrosion associated the...  
WO/2015/062966A1
The invention concerns a method of operating a gas turbine (100) in order to ensure that a gas turbine operates reliably and economically in natural gas supply mains with a power-to-gas feed. To that end, the hydrogen content of the fuel...  

Matches 151 - 200 out of 8,405