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Matches 1 - 50 out of 30,352

Document Document Title
WO/2017/007530A1
A turbine engine duct assembly (80) including a joint assembly (86) having an outer shroud (100), a bellows (106), a flared tube (120), a backing ring (122), and a kinematic ring (128). The joint assembly provides for dynamic movement of...  
WO/2017/005425A1
The invention relates to an exhaust gas system (1), comprising: an exhaust gas channel (4), which is provided with insulation (3) on the inner face (2) of the exhaust gas channel; and a catalyst (5) for reducing emissions, which is arran...  
WO/2017/005997A2
The invention relates to a reduction gear (11) having an epicyclic gear train for a turbine engine (1), in particular of an aircraft, comprising: a planetary shaft (15) having an axis of rotation A; a ring gear (19) having an axis A exte...  
WO/2017/007529A1
A turbine engine duct assembly and joint assembly having an outer shroud at least partially defining an interior of the joint assembly, an inner shroud at least partially received within the outer shroud and forming an interface therewit...  
WO/2017/007068A1
A combustor comprises: a combustion can in the form of a can having a combustion space where fuel is combusted, the combustion can including an inlet through which fuel is introduced, an outlet through which gas produced from the combust...  
WO/2017/004644A1
Assembly comprising a synchronous generator (1) for converting mechanical power into electric power, said synchronous generator having a predefined number of pairs of poles, the assembly further comprising an asynchronous machine (2) tha...  
WO/2017/006690A1
A combustor nozzle, a gas turbine combustor, a gas turbine, a cover ring, and a method for manufacturing a combustor nozzle, wherein there are provided: a nozzle body (71) to which a fuel channel (72) is provided; a cover ring (75) dispo...  
WO/2017/007802A1
A support structure for rotating machinery is provided. The support structure may include a first main hollow support member and a second main hollow support member, each having a longitudinal axis and a square cross-section. The second ...  
WO/2017/005427A1
The invention relates to a cooling device (1) for use in a power plant, comprising at least two controllable fans (11, 12), which are designed to produce an air flow (13, 14) having a specified flow direction (R1, R2) during operation, a...  
WO/2017/007809A2
A motive air conditioning system for a gas turbine assembly is provided. The motive air conditioning system may include an inlet flow channel configured to be fluidly coupled with the gas turbine assembly. The motive air conditioning sys...  
WO/2017/006927A1
Provided is a high-strength, heat-resistant, Ni-base alloy member comprising Co: 5 to 12%, Cr: 5 to 12%, Mo: 0.5 to 3.0%, W: 3.0 to 6.0%, Al: 5.5 to 7.2%, Ti: 1.0 to 3.0%, Ta: 1.5 to 6.0%, Re: 0 to 2.0%, and C: 0.01 to 0.20%. The balance...  
WO/2016/207828A2
The present embodiments disclose a method of running an air inlet system upstream of one or more inlet air filters of a device protected by air filtration, wherein the method comprises: regulating the relative air humidity of the inlet a...  
WO/2016/208211A1
The vibration reduction damper (13) according to the present disclosure is disposed in the interior of a center vent tube (12) having vent holes (12a) which penetrate in the radial direction, and is provided with a sliding part (13a) tha...  
WO/2016/207829A1
The present embodiments disclose a system (100) for reducing inlet air temperature of a device, comprising: a fogging system that provides air cooling, wherein the fogging system comprises at least one low pressure atomiser (110).  
WO/2016/209825A1
The subject matter of this specification can be embodied in, among other things, a fluid flow trim apparatus includes an outer housing defining a cavity having an interior surface and an end wall having an orifice therethrough, a valve b...  
WO/2016/208998A1
A method for controlling a gas turbine combustor, according to one embodiment for achieving the objective of the present invention, may comprise: a detection step of obtaining combustion oscillation values through first detection units p...  
WO/2016/208952A1
A fuel supply nozzle unit disclosed herein comprises: a fuel supply nozzle that includes a front end portion having a plurality of fuel supply holes formed therein, a rear end portion extending from the front end portion and having a thr...  
WO/2016/204534A1
A combustion duct assembly for a gas turbine, according to the present invention, comprises: a liner at which a combustor is disposed at the upper side thereof and an annular spring seal protruding outward is attached to the outer surfac...  
WO/2016/204893A1
Apparatus, systems, and methods use cryogenic liquids such as, for example, liquefied natural gas and liquefied air or liquefied air components to store thermal energy. The cryogenic liquids may be produced using electrically powered liq...  
WO/2016/199422A1
An exhaust gas diffuser is provided with: a plurality of struts extending through an inner cylinder and an outer cylinder and connecting a bearing support which is disposed inside the inner cylinder and a structure which is disposed outs...  
WO/2016/200915A1
An airplane is provided. The airplane includes a pressurized compartment and an environmental control system. The environmental control system includes a compressing device. The compressing device includes a compressor and a turbine. The...  
WO/2016/199319A1
[Problem] To provide a turbine that has a simple structure, that is composed of a CMC and achieves a wide range of gas flow passages while suppressing thermal stress acting on turbine stator blades, and that can consequently realize furt...  
WO/2016/195968A1
Apparatus, systems, and methods store energy by liquefying a gas such as air, for example, and then recover the energy by regasifying the liquid and combusting or otherwise reacting the gas with a fuel to drive a heat engine. The process...  
WO/2016/193596A1
A device for cooling a rolling bearing (112), in particular for a turbine engine, the device comprising an annular bearing support (124) comprising a substantially cylindrical wall (134) of which an inner peripheral face (136) is configu...  
WO/2016/194677A1
A sealing device for minimizing leakage of a fluid flowing through an annular gap between a stationary member and a rotating member of a rotating machine comprises an annular fixed fin provided to the annular gap, and an annular movable ...  
WO/2016/193724A1
A micro-CHP gas boiler comprises a heat exchanger having a combustion space surrounded by a water flowpath, and a gas turbine assembly which is installed in the combustion space. The gas turbine assembly includes a generator surrounded b...  
WO/2016/192890A1
The invention relates to an operating method for a gas turbine (1) by partial-load operation, comprising the following steps: setting of a power setpoint value (LS) for a predefined temperature value (T0); determining the two operating c...  
WO/2016/194742A1
A combined cycle plant, a device for controlling a combined cycle plant, and a method for activating a combined cycle plant, wherein the time for starting up the combined cycle plant can be shortened by providing: a gas turbine (11) havi...  
WO/2016/195999A1
Apparatus, systems, and methods store energy by liquefying a gas such as air, for example, and then recover the energy by regasifying the cryogenic liquid and combusting or otherwise reacting the gas with a fuel to drive a heat engine. C...  
WO/2016/189712A1
This jet engine (1) is provided with: a fan (3, 31, 32, 33) having moving blades (3b1, 3d1, 3g1, 3i1, 3k1) in a plurality of stages; compressors (4, 5) which compress air fed from the fan (3, 31, 32, 33); a combustor (6) which generates ...  
WO/2016/189234A1
Turbine engine unit for lubricating a bearing holder A turbine engine unit is provided, including: an inter-turbine housing that includes a hub (1) including a bearing holder, a ferrule (2) extending around and at a distance from the hub...  
WO/2016/189188A1
A power plant (10) comprising a first turbine-compressor unit (12) provided with a first compressor part (14) and a first turbine part (20); a gas heater unit (24) arranged in fluid connection with the first compressor part (14) and the ...  
WO/2016/190510A1
A combustion liner includes air guiding caps which are respectively engaged to a mounting member and are turned in a flow direction of air so as to collect a fluid flowing around the combustion liner and feed it to the combustion liner, ...  
WO/2016/189189A1
A power plant (10) comprising a first turbine-compressor unit (12) provided with a first compressor part (14) and a first turbine part (20); a gas heater unit (24) arranged in fluid connection with the first compressor part (14) and the ...  
WO/2016/189026A1
The present invention concerns a method for assembling equipment on a support (100) of a turbo-machine. The method comprises the step of mechanically assembling the equipment to a part (101) of said support (100) by means of a fastening ...  
WO/2016/184415A1
A miniature turbojet engine, comprising a turbine machine (1), a compressor (2), a rotary shaft (3), two radial bearings (4), a thrust bearing (5) and a combustion chamber (6), the radial bearings (4) being mixed-type dynamic pressure ga...  
WO/2016/184412A1
An ultra-high speed gas turbine generator, comprising a turbine machine (1), a compressor (2), a motor (3), two radial bearings (4a, 4b), a thrust bearing (5) and a combustion chamber (6), the radial bearings (4a, 4b) being groove-type d...  
WO/2016/186512A1
A system and a method for recovering waste heat from an industrial process in pre heating combustion air and fuel is provided. The present invention attains the above-described objective by a plurality of heat exchangers extracting heat ...  
WO/2016/184413A1
A miniature gas turbine generator, comprising a turbine machine (1), a compressor (2), a motor (3), two radial bearings (4a, 4b), a thrust bearing (5) and a combustion chamber (6), the radial bearings being mixed-type dynamic pressure ga...  
WO/2016/184414A1
An ultra-high speed turbojet engine, comprising a turbine machine (1), a compressor (2), a rotary shaft (3), two radial bearings (4), a thrust bearing (5) and a combustion chamber (6), the radial bearings (4) being groove-type dynamic pr...  
WO/2016/185732A1
A guide surface which expands to the outer peripheral side as the guide surface extends from the upstream side to the downstream side is formed on a support section. A guided surface which expands to the outer peripheral side as the guid...  
WO/2016/184678A1
The invention concerns a steam turbine foundation (10) adapted to support a steam turbine system (100). The steam turbine foundation (10) comprises a base plate (12), a first support (20), a second support (30) and a third support (40). ...  
WO/2016/181420A1
A mount mechanism (3) for mounting an accessory gearbox (11) to the engine case of an aircraft engine comprises: a pair of first brackets (4) affixed to either the engine case or the accessory gearbox (11) and located at a distance from ...  
WO/2016/180808A1
A containment sleeve (23) of a turbomachinery bearing (22), the sleeve (23) comprising a body defining a surface (23A) configured to support a turbomachinery bearing (22), and at least a first (25A) and a second hole (25B) opening on sai...  
WO/2016/182785A1
A grommet (341) for a combustion chamber (320) of a gas turbine engine (100) is disclosed. The grommet (341) includes a lower platform (352) and a collar (351). The lower platform (352) includes a plurality of top slots (347) located in ...  
WO/2016/177644A1
There is disclosed a turboshaft engine (10) having a principal rotational axis and comprising a power turbine (16), a tail bearing housing (18) and an exhaust collector (19) arranged in axial flow series along said axis. The tail bearing...  
WO/2016/174341A1
The invention relates to a turboshaft engine for a helicopter, comprising a case (5) inside which a gas generator (6) and a turbine (7) are accommodated, the turbine (7) being mounted on a power shaft (8) that extends along a longitudina...  
WO/2016/176174A1
The invention relates generally to an electrical power and storage system and more specifically to ways and methods of using a thermal storage medium as a heat source to heat compressed air from a power augmentation system for use in a g...  
WO/2016/175753A1
A fuel delivery system (10) for a gas turbine engine (12) that employs a technique for purging fuel delivery tubes (82). The fuel delivery system includes a multifunction valve (64) that has a flow through position (66) and a bi-directio...  
WO/2016/175072A1
A rotor shaft (21) has formed therein: an inlet flow passage (34d) for allowing gas in a gas compression flow passage (19) to flow into the outer cavity (24) of a downstream cavity group (22d); a radial flow passage (35) for connecting t...  

Matches 1 - 50 out of 30,352