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Patent Searching and Data


Matches 201 - 250 out of 8,405

Document Document Title
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...  
WO/2015/014508A1
The invention relates to a gas turbine power plant (1), comprising a gas turbine (10). Said gas turbine comprises a compressor (11), a combustion chamber (12), and an expander (13) and is rotationally mechanically coupled to an energisat...  
WO/2015/017042A1
A gas turbine engine includes a core housing that includes an inlet case and an intermediate case that respectively provide an inlet case flow path and an intermediate case flowpath. A shaft provides a rotational axis. A hub is operative...  
WO/2015/011645A1
Heat and electricity generating apparatus (201) for a boiler system (202) for use in a residential or small-scale building. The heat and electricity generating 5 apparatus (201) comprises a centrifugal air compressor (203), a turbo-expan...  
WO/2015/012923A3
A turbofan engine includes a geared architecture for driving a fan about an axis. The geared architecture includes a sun gear rotatable about an axis, a plurality of planet gears driven by the sun gear and a ring gear circumscribing the ...  
WO/2015/012923A2
A turbofan engine includes a geared architecture for driving a fan about an axis. The geared architecture includes a sun gear rotatable about an axis, a plurality of planet gears driven by the sun gear and a ring gear circumscribing the ...  
WO/2015/010047A1
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/2015/002686A2
A liner panel for a combustor of a gas turbine engine includes a multiple of heat transfer augmentors. At least one of the multiple of heat transfer augmentors includes a hemi-spherical protuberance.  
WO/2015/002680A2
In various embodiments, a manifold assembly (64) for conducting one or more fluids to a gear assembly (60) in a gas turbine engine (20) is provided. The manifold assembly (64) may comprise a first plate (66) and a second plate (68) that ...  
WO/2015/002686A3
A liner panel for a combustor of a gas turbine engine includes a multiple of heat transfer augmentors. At least one of the multiple of heat transfer augmentors includes a hemi-spherical protuberance.  
WO/2014/209659A1
A system includes an oxidant compressor and a gas turbine engine turbine, which includes a turbine combustor, a turbine, and an exhaust gas compressor. The turbine combustor includes a plurality of diffusion fuel nozzles, each including ...  
WO/2014/207035A1
A method and a plant for capturing CO2 from an incoming exhaust gas, are described. The incoming exhaust gas (1) is compressed (3, 3'), introduced into a combustion chamber (18) together with natural gas (6), and partly expanded (9). The...  
WO/2014/210079A1
A method of controlling an exhaust gas recirculation (EGR) gas turbine system includes adjusting an angle of a plurality of inlet guide vanes of an exhaust gas compressor of the EGR gas turbine system, wherein the plurality of inlet guid...  
WO/2014/210081A1
A system includes a plurality of extraction passages configured to passively extract a portion of a gas flow from a downstream region of a gas flow path. The system includes a plurality of sensors respectively coupled to the plurality of...  
WO/2014/210409A1
An exemplary embodiment of the present techniques provides a system for decreasing a temperature of a fluid. The system includes an axial flow expander for expanding gas flowed in a direction along an axis thereof. The axial flow expande...  
WO/2014/204574A2
The present disclosure relates to a first seal for an aircraft blade outer air seal ("BOAS") comprising a first portion comprising a first channel and a second channel, and a second portion comprising a first projection and a second proj...  
WO/2014/200582A1
A method and apparatus of using cryogenic fuel (12) in an engine (101) for an aircraft (5) wherein the cryogenic fuel (12) is supplied to the engine for combustion.  
WO/2014/200588A2
A combustor of a gas turbine engine includes an additively manufactured liner panel with a heat transfer augmentation feature.  
WO/2014/200588A3
A combustor of a gas turbine engine includes an additively manufactured liner panel with a heat transfer augmentation feature.  
WO/2014/197045A3
A liner assembly for a combustor of a gas turbine engine according to one disclosed non-limiting embodiment of the present disclosure includes a grommet with a multiple of grommet cooling passages.  
WO/2014/197045A2
A liner assembly for a combustor of a gas turbine engine according to one disclosed non-limiting embodiment of the present disclosure includes a grommet with a multiple of grommet cooling passages.  
WO/2014/197089A2
A flow transfer apparatus for transferring cooling flow from a primary gas flowpath (P) to a turbine rotor (128). The apparatus includes: a first supply plenum (92) communicating with the primary gas flowpath (P) and first inducers (148 ...  
WO/2014/189603A3
A gas turbine engine comprising a combustion system configured for continuous detonation combustion process, the process employing a rotating continuous detonation wave (70).  

Matches 201 - 250 out of 8,405