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Patent Searching and Data


Matches 201 - 250 out of 8,497

Document Document Title
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...  
WO/2015/064193A1
An exhaust heat recovery device (5) having an exhaust heat recovery coil (14), a denitration device (15), a latent heat recovery device (6) having a latent heat recovery coil (17), and a condensed water recovery unit (8) connected to the...  
WO/2015/066671A2
Systems, apparatus, and methods are disclosed that include a divided exhaust engine with at least one primary EGR cylinder and a plurality of non-primary EGR cylinders. The systems, apparatus and methods control the amount of recirculate...  
WO/2015/065579A1
A liner panel within a gas turbine engine includes a perimeter rail that defines a first height from a cold side. The liner panel also includes an intermediate rail that defines a second height from the cold side, where the second height...  
WO/2015/060902A1
A fuel supply manifold of a gas turbine engine, a method for assembling a fuel supply manifold for a gas turbine engine, and a gas turbine engine are disclosed. The fuel supply manifold for the gas turbine engine man include a plurality ...  
WO/2015/054834A1
A fuel supply system includes a first fuel gas compressor coupled to a fuel gas compressor shaft and configured to pressurize a fuel for a gas turbine system. A clutch is coupled to the fuel gas compressor shaft and is configured to sele...  
WO/2015/057284A3
A portable on-demand hydrogen supplemental system (1) for a gas turbine jet engine (205), producing hydrogen gas and mixing the hydrogen gas with the air used for combustion of the jet fuel to increase the combustion efficiency of said j...  
WO/2015/054140A1
An assembly is provided for a turbine engine. The assembly includes a fuel injector and a fuel vaporizer. A nozzle of the fuel injector is adapted to direct fuel to impinge against the fuel vaporizer. The fuel vaporizer is adapted to sub...  
WO/2015/054115A1
A combustor wall is provided for a turbine engine and includes a combustor shell and a heat shield. The heat shield is attached to the shell with first and second cavities extending between the shell and the heat shield. The first cavity...  
WO/2015/053003A1
Provided is a fuel injection device for gas turbines that is capable of uniformizing, with a simple structure and at low cost, the concentration distribution of a fuel gas and water vapor in a combustion chamber, and that is capable of e...  
WO/2015/054136A1
An assembly is provided for a turbine engine. The assembly includes a cooling tube through which a flow path extends. The assembly also includes a fuel injector, which includes a stem connected to a tip. The stem is arranged within the c...  
WO/2015/054244A1
A combustor wall is provided for a turbine engine. The combustor wall includes a shell, a heat shield and a combustion chamber. The heat shield is connected to the shell by a bonded connection, and defines a portion of the combustion cha...  
WO/2015/053004A1
Provided is a fuel injection device for gas turbines that is capable of uniformizing, with a simple structure and at low cost, the concentration distribution of a fuel gas and water vapor in a combustion chamber, and that is capable of e...  
WO/2015/049453A1
Jet pump (10) for a device for depressurizing a turbomachine lubricating chamber, comprising a tubular body (12), a first injection duct (14) which opens into the body (12) via a first outlet nozzle (18), a second injection duct (16) whi...  
WO/2015/050879A1
A combustor wall is provided for a turbine engine. The combustor wall includes a combustor shell and a combustor heat shield that is attached to the shell. The heat shield includes a first panel and a second panel that sealingly engages ...  
WO/2015/050576A1
A gas turbine engine comprises a fan drive turbine. The fan drive turbine drives the fan through a gear reduction; A change in enthalpy is defined across the gas turbine engine. The change in enthalpy divided by a speed of the fan drive ...  
WO/2015/048628A1
In various aspects, a method for producing electricity by operating two or more turbines in series is provided. The method can include introducing, at least part of, the exhaust from an upstream turbine into a combustion chamber of a dow...  
WO/2015/043568A1
The present invention relates to a drive apparatus which has an engine and a thrust nozzle for generating thrust in a first direction. Furthermore, the engine and the thrust nozzle are connected to one another by a thrust nozzle pipe. Th...  
WO/2015/038768A1
An industrial gas turbine engine for electrical power production includes a high pressure spool and a low pressure spool in which the low pressure spool can be operated from full power mode to zero power mode when completely shut off, wh...  
WO/2015/036703A1
The invention relates to a method (1000) for monitoring a degree of coking at dynamic seals of a turbine engine comprising: a gas generator including a rotary shaft and an injection wheel mounted on the shaft; a fuel injection manifold d...  
WO/2015/031796A1
A hybrid diffuser case for a gas turbine engine includes an outer diffuser case wall that extends downstream from an annular outer pre-diffuser case shroud. An inner diffuser case wall extends downstream from an annular inner pre-diffuse...  
WO/2015/031816A1
A wall assembly for a combustor of a gas turbine engine is provided. The wall assembly includes a support shell with a contoured region to define at least one convergent passage between the support shell and a multiple of liner panels. A...  
WO/2015/030927A1
A wall assembly for use in a combustor of a gas turbine engine includes a support shell with a first inner periphery along an axis and a liner panel with a second inner periphery along the axis. The second inner periphery is smaller than...  
WO/2015/023764A1
A bulkhead assembly for a combustor of a gas turbine engine includes a bulkhead support shell with a multiple of swirler openings. Each of the multiple of swirler openings is surrounded by a first multiple of cooling impingement passages...  
WO/2015/021522A1
The invention is characterized by a rotary external housing and the attachment of the movable blades inside said housing, and by the attachment of the fixed (or static) blades to a shaft or other immovable central element, irrespective o...  
WO/2015/017058A1
A system includes a compressor configured to compress a gaseous stream, an exhaust gas cooler configured to cool an exhaust gas from combustion with a cooling water, and a water injection system configured to inject the cooling water fro...  
WO/2015/017080A1
A system includes a gas turbine engine that includes a combustor section having a turbine combustor that generates combustion products, a turbine section having one or more turbine stages driven by the combustion products, an exhaust sec...  
WO/2015/017059A1
A system includes an oxidant compressor and a gas turbine engine. The gas turbine engine includes a combustor section having a turbine combustor, a turbine driven by combustion products from the turbine combustor, and an exhaust gas comp...  
WO/2015/017454A1
In one embodiment, a system includes a turbine combustor having a combustor liner disposed about a combustion chamber, a head end upstream of the combustion chamber relative to a downstream direction of a flow of combustion gases through...  

Matches 201 - 250 out of 8,497