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Matches 1 - 50 out of 32,721

Document Document Title
WO/2017/213816A1
A gas turbine engine and method of operation are provided. The gas turbine engine may include a variable geometry component operably driven by a component actuator. The component actuator may be in fluid communication with a primary line...  
WO/2017/213113A1
Corrosion resistance is enhanced while ensuring high enough heat shielding performance and erosion resistance. The present invention is provided with: a highly porous layer (6) that is formed on a heat-resistant substrate (100), that is ...  
WO/2017/213848A1
A maintenance access system for a gas turbine. The maintenance access system includes an enclosure and an inlet wall assembly coupled to the enclosure by a pivotal connector. The maintenance access system further includes a pair of rails...  
WO/2017/212211A1
A radial flow turbine heat engine (2) includes a compressor (6), a recuperator (10), a combustor (12) and a turbine (8). A compressor outlet manifold (14) collects compressed gas from the compressor through a plurality of compressor outl...  
WO/2017/207890A1
The invention relates to an intermediate turbomachine casing comprising at least a central hub and a shell (12) which are disposed concentrically to one another and connected mechanically by structural arms (11), said casing comprising a...  
WO/2017/209167A1
An acquisition unit acquires a measurement value of a target device. A likelihood calculation unit calculates, on the basis of the measurement value acquired by the acquisition unit, the likelihood of occurrence of each of a plurality of...  
WO/2017/209127A1
Provided is a structure that cools a constituent member (5) of a gas turbine (GT) using a working gas (A), wherein: a plurality of heat transfer enhancement ribs (15), each in the shape of a letter W, are provided protruding from a wall ...  
WO/2017/209018A1
In order to reduce the amount of leakage of a fluid, this labyrinth seal (30) is equipped with: an increased-diameter step part (41), which is a high-pressure-side (X1) step part; a reduced-diameter step part (42), which is a low-pressur...  
WO/2017/207902A1
The invention relates to an inlet body (3) for a fluid injector (1) for a turbomachine. The inlet body (3) comprises a casing (30) defined by an internal surface (31) and a seal valve (6) housed inside the casing (30). The valve (6) comp...  
WO/2017/207901A1
The invention relates to an inlet body for a fluid injector for a turbomachine. The inlet body comprises a casing and an inlet nozzle (50), housed inside the casing, and configured to serve as a seat for a mobile sealing member (20). The...  
WO/2017/206084A1
The invention discloses a regenerative cycle gas turbine system and a combined cooling heating and power system. The regenerative cycle gas turbine system comprises an air compressor, an air regenerator, a combustion chamber, a turbine, ...  
WO/2017/209179A1
An acquisition unit acquires a measurement value of a target device. The acquired measurement value includes at least: the temperature and the flow rate of an input fluid that is input to the target device; and the temperature and the fl...  
WO/2017/203917A1
Provided is a rotating body comprising: an impeller having a body 21, the impeller also having a surface 23 on which welding is to be performed, the surface 23 being provided on the rear surface 21b of the body 21, the impeller further h...  
WO/2017/204949A1
A gas turbine engine includes a combustion section, the combustion section including a plurality of fuel nozzles. A fuel delivery system for the gas turbine engine includes a feed tube and a fuel manifold fluidly connected to the feed tu...  
WO/2017/203155A1
The invention relates to an aircraft turbine engine, including at least one rotary body comprising a compressor rotor and a turbine rotor connected to one another by a rotor shaft, the turbine engine being configured to drive a member by...  
WO/2017/204941A1
The low pressure turbine includes a rotor, an outer casing, a plurality of stages of rotor blades, and a plurality of stages of stator vanes. The rotor includes a longitudinal centerline. The outer casing circumscribes the rotor. The plu...  
WO/2017/200644A1
An apparatus and method of cooling a rotatable member, in particular the rotor of a gas compressor forming part of a gas turbine, enclosed within a casing are provided. The gas compressor includes a rotor (234), a plurality of stages of ...  
WO/2017/199981A1
A wireless power supply device which supplies power in a non-contact manner from a stator side to a plurality of power receiving antennas disposed spaced apart in a circumferential direction on a rotor which rotates about an axis O is pr...  
WO/2017/198999A1
A compressor system for a turbo machine (10), comprising a low pressure shaft (36) coupled to a low pressure turbine (34), and a high pressure shaft (38) coupled to a high pressure turbine (32). The compressor system may comprise a fan (...  
WO/2017/201279A1
A fan casing assembly for a turbine engine including a casing having an annular fan cooler. The annular fan cooler includes first and second connection assemblies to fix movement of the fan cooler during engine operation, while permittin...  
WO/2017/200665A1
A gas turbine engine includes a core engine, a low pressure turbine, a fan assembly, a gearbox, and a lubrication scavenge pump. The core engine includes a high pressure compressor, a combustor, and a high pressure turbine configured in ...  
WO/2017/198965A1
The invention relates to a reversible system (2) for dissipating thermal power generated by a gas-turbine engine, comprising a first heat exchanger (6) forming a condenser, a second heat exchanger (8) forming an evaporator, a spiral comp...  
WO/2017/196356A1
A method, including: operating an industrial gas turbine engine having a plurality of combustor cans (100) arranged in an annular array, each can having burner stages (122, 124, 132) and a pilot burner arrangement (104) having a premix p...  
WO/2017/194866A1
The invention relates to a rotating front part (1) of an aircraft turbomachine intake comprising bolts (34) for attaching a cone tip (20a) to an internal support (24), each bolt comprising a rear end (50) that is screwed into the support...  
WO/2017/195575A1
This seal segment (11) is provided with: a retainer (21); a seal body (13) comprising a thin plate seal piece (20); a high pressure-side side plate (23); a low pressure-side side plate; and a block body (50) that comprises a retainer sim...  
WO/2017/195518A1
Provided is a coating structure, a turbine part having the same, and a method for manufacturing the coating structure. The coating structure is provided on a surface of a base portion including a ceramic-based composite material. The coa...  
WO/2017/195550A1
This seal segment (11) is provided with: a seal body comprising a plurality of layered thin plate seal pieces (20); and a high pressure-side side plate (23). The high pressure-side side plate (23) comprises: an outer diameter-side edge (...  
WO/2017/196563A1
An aspirating face seal between high and low pressure regions of a turbomachine at a juncture between rotatable and non-rotatable members of turbomachine includes gas bearing rotatable and non-rotatable face surfaces. Starter seal tooth ...  
WO/2017/195704A1
A seal segment (11) is provided with: a retainer that extends on the outer circumferential side of a rotating shaft in the circumferential direction (Dc) of the rotating shaft; a first seal body (13) that extends inward in the radial dir...  
WO/2017/187078A1
The invention relates to an auxiliary system for mechanically driving a relay shaft (8) of a helicopter propulsion system, comprising: a hydraulic motor (7), mechanically connected to said relay shaft (8); a hydraulic circuit (10) for su...  
WO/2017/188039A1
The present invention reduces pressure loss in compressed air that is supplied from a compressor to a combustion cylinder. A compressor diffuser (5), wherein one end (51) thereof is connected to an exit port (16) of a compressor (1), the...  
WO/2017/188040A1
The present invention reduces pressure loss in cooling air that is supplied to turbine stator blades. The present invention comprises: a cooling device (7) that generates cooling air by extracting and cooling compressed air (P) from a co...  
WO/2017/187079A1
The invention relates to a mechanical drive device comprising an ignition system having a control device (124), a laser diode (130) capable of emitting an optical signal in the event of receiving a firing command, an optical line (140) c...  
WO/2017/188052A1
The integrated gasification combined cycle power generation plant comprises: a gasification furnace; a gas turbine which is configured to be drivable by using combustible gas generated by the gasification furnace as fuel; a flow rate con...  
WO/2017/189217A1
An in-line propeller gearbox of a turboprop gas turbine engine includes a lubricant reservoir disposed spaced radially offset from the engine's central axis of rotation and asymmetrically with respect to the central axis of rotation such...  
WO/2017/187082A1
The invention relates to a jet pump for a system for supplying fluid to a turbomachine. The jet pump comprises an active fluid inlet pipe (5) comprising a tube (50) delimiting the inlet pipe (5), and a passive fluid inlet pipe that is fl...  
WO/2017/189440A1
An industrial gas turbine engine with a high spool and a low spool in which low pressure compressed air is supplied to the high pressure compressor, and where a portion of the low pressure compressed air is bled off for use as cooling ai...  
WO/2017/187091A1
To facilitate the removal of a bearing housed in an arm of a turbomachine casing, which bearing guides a transmission shaft of the turbomachine, the invention provides a casing arm (50) comprising a body (100) consisting of a vertical po...  
WO/2017/182334A1
The invention relates to an energy conversion system for a turbomachine, characterized in that at least one transmission (10, 20a, 20b, 20c) and/or at least one bearing housing (40) is thermally coupled to at least one thermoelectric ele...  
WO/2017/182532A1
An assembly has a supporting element4, rotatable about an axis 7, and an oil transfer unit 1, whichhas a stationary part 18 and a rotating part 19,coupled inan angularly fixed position to the supporting member 4 and defining an inner cha...  
WO/2017/181803A1
A method for quick restart of an engine, comprising: determining, when an engine stalls, whether the engine satisfies a preset quick restart condition; if the preset quick restart condition is satisfied, starting a starter to maintain a ...  
WO/2017/183063A1
The turbine component according to an embodiment comprises a base material configured from an Fe-based alloy containing at least one element selected from the group consisting of Cr, Si, and Al. The base material has, from the interior o...  
WO/2017/184411A1
The present application relates to a fluid damped air bearing (200, 234) for a turbomachine; the turbomachine comprises an outer ring disposed radially outward from a housing (330) of the bearing, and a plurality of airfoils disposed bet...  
WO/2017/184364A1
The present embodiments describe a method to reduce vanadium corrosion in a gas turbine by adding an oleophilic corrosion inhibitor into a combustion fuel, in which the oleophilic corrosion inhibitor comprises carbon black support partic...  
WO/2017/178185A1
A turbomachine train (9) with two shaft parts which each have a fixedly attached grooved wheel (5), with a first overrunning clutch (7), with two rotational speed sensors and with a control device. The clutch is designed to couple and de...  
WO/2017/180295A1
A fuel injector (26) for a combustion engine (10) includes an injector head (28) including a nozzle (44), a premixer (48), and a distributor (70) structured to distribute a plurality of different fuels to different sets of fueling orific...  
WO/2017/180294A1
A fuel injector (26) for a combustion engine (10) includes an injector head (28) including a nozzle (44), a premixer (48), and a distributor (70) structured to distribute a plurality of different fuels to different sets of fueling orific...  
WO/2017/180296A1
A fuel injector (26) for a combustion engine (10) includes an injector head (28) including a nozzle (44), a premixer (48), and a distributor (70) structured to distribute a plurality of different fuels to different sets of fueling orific...  
WO/2017/177229A1
A turbomachine sealing component has: a substrate having circumferential surface; and a coating on the circumferential surface. The coating or a layer thereof is patterned to form circumferential sealing ridges.  
WO/2017/175563A1
Provided are a nickel-base alloy having high high-temperature strength, a turbine blade using same, and a method for producing an injection molded article of the nickel-base alloy. The nickel-base alloy (10) contains: at least one metal ...  

Matches 1 - 50 out of 32,721