Login| Sign Up| Help| Contact|

Patent Searching and Data


Matches 201 - 250 out of 8,618

Document Document Title
WO/2015/177296A1
The invention relates to a device and a method for treating a gas flow. Combustible components are separated from a first gas flow by means of an absorption process using a liquid medium in an absorption device; the components dissolved ...  
WO/2015/172899A1
The invention relates to a method for operating a burner (16), wherein a fuel (84) and an oxidizing working medium (86) are fed into the burner (16), the fuel (84) and the working medium (86) are introduced into a combustion volume (14) ...  
WO/2015/174246A1
By using a combustion exhaust gas (18) from a power turbine (16), a high-pressure secondary compressed air (12C) is subjected to heat exchange in a first heat exchange unit (19A) of an exhaust heat recovery device (19), and by using resu...  
WO/2015/161972A1
The invention relates to a method for exhaust gas aftertreatment, in which an exhaust gas to be aftertreated, which is produced during a combustion process, is treated with a reducing agent. The invention further relates to a combustion ...  
WO/2015/156889A2
A mid-turbine frame (MTF") for a jet engine is disclosed and comprises a duct that extends between a high pressure turbine ("HPT") and a low pressure turbine ("LPT"), the duct comprising a plurality of segments that together form an oute...  
WO/2015/155142A1
The invention relates to a gas turbine (100) assembly comprising a first shaft (101), a first compressor (102) and a first turbine (103) mounted on the first shaft, a combustor (104) between the first compressor (102) and the first turbi...  
WO/2015/155818A1
This floating liquefied-gas production facility (1) is equipped with: a gas turbine unit (20); a liquefaction facility (90) that has a primary refrigeration compressor (40) driven by the gas turbine unit (20), and cools natural gas; a dr...  
WO/2015/155450A1
The invention concerns a device for assisting a propulsion system of a single-engine helicopter comprising an engine linked to a power transmission unit (15) suitable for rotating a rotor of the helicopter, characterised in that it compr...  
WO/2015/149447A1
Provided is a thermodynamic cycle method and system for a semi-closed constant pressure internal combustion in a prime motor. The cycle process thereof comprises a multi-stage compression interstage cooling process, a counter-flow heat e...  
WO/2015/149448A1
Provided is a method and system for a semi-closed timing constant volume thermodynamic cycle in a prime motor. The cycle thereof comprises 6 processes: a multi-stage compression interstage cooling process, a counter-flow heat exchange pr...  
WO/2015/147938A3
A combustor wall assembly has a heat shield and a supporting shell with a cooling cavity defined therebetween. A grommet generally includes a wall defining a dilution hole isolated from the cooling cavity, and a flange projecting radiall...  
WO/2015/145041A1
The invention relates to a method for detecting a failure of a first turbine engine, referred to as faulty engine (4), of a twin-engine helicopter and for operating a second turbine engine, referred to as sound engine (5), each engine (4...  
WO/2015/145043A1
The invention relates to a turboshaft engine comprising a gas generator (5) designed to be rotated and a free turbine (6) rotated by the gases from the gas generator (5). The turboshaft engine is characterised in that it comprises a devi...  
WO/2015/147974A1
A system, including: a recirculated exhaust gas conditioning loop that routes exhaust gas from a heat recovery steam generator to a turbine compressor inlet, wherein the recirculated exhaust gas conditioning loop includes an exhaust gas ...  
WO/2015/148855A1
An engine, a biomass powder energy conversion and/or generation system, hybrid turbine engines, and methods of manufacturing and using the same are disclosed. The engine includes a housing having an inner wall and an outer wall, a centra...  
WO/2015/147938A2
A combustor wall assembly has a heat shield and a supporting shell with a cooling cavity defined therebetween. A grommet generally includes a wall defining a dilution hole isolated from the cooling cavity, and a flange projecting radiall...  
WO/2015/145077A1
Assistance device (100) for a free turbine turbomachine (TAG1) of an aircraft comprising at least two free turbine turbomachines (TAG1, TAG2), the device comprising an electric starter machine (D1) for providing prolonged assistance to t...  
WO/2015/146170A1
[Problem] To control the temperature of dehydrogenation to an appropriate range to enable efficient and stable hydrogen generation when exhaust gas of power generation is used as a heat source for the dehydrogenation. [Solution] A hydrog...  
WO/2015/145076A1
Assistance device (100) for an aircraft free turbine turbomachine (TAG1), the device comprising means (K11, CVS1) for electrically powering a coil (SU) of a rotary starter machine (GD1), referred to as first coil, in order to provide a f...  
WO/2015/145045A1
The invention relates to a turboshaft engine comprising a gas generator (5) designed to be rotated and a free turbine (6) rotated by the gases from the gas generator. The turboshaft engine is characterised in that it comprises a device (...  
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...  

Matches 201 - 250 out of 8,618