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Matches 1 - 50 out of 31,223

Document Document Title
WO/2017/137740A1
The invention concerns a noise attenuation panel comprising a sound absorbing honeycomb layer disposed between a perforated surface layer on an airflow facing side of the panel and a composite support layer on a second opposing side of s...  
WO/2017/139222A1
A fuel injector (32) for a combustion engine (10) includes an injector body (34) having formed therein a first passage (50) structured to feed a fuel to an outlet (40) of the injector body (34), and a second passage (52) structured to fe...  
WO/2017/137404A1
The invention relates to a method for operating a heat engine, which permits a reliable operation of the heat engine, in particular under variable boundary conditions, wherein the method comprises the following steps: supplying gas conta...  
WO/2017/137701A1
The invention relates to a system for rotating a fan (2) of a turbojet engine (1) about a first rotation axis (Ω), including a reduction gear (3) made up of a planetary gearset placed at the centre of the fan (2), which includes: a cent...  
WO/2017/137227A1
The invention relates to a power plant (1) comprising a gas turbine (2) and a generator (3) which are arranged on a section (18), a shaft (4) which connects the gas turbine (2) to the generator (3) in order to transmit a force, and a clu...  
WO/2017/134976A1
A method for implementing an abradable coating comprising: a pattern-forming step S1 in which, using a slurry containing ceramic particles and solvent, a slurry pattern is formed on the surface of a thermal barrier coating layer; and a f...  
WO/2017/134844A1
Provided is an aircraft component used in a gas turbine engine for an aircraft, the aircraft component comprising an annular part having an outer peripheral surface, and a boss part (7) that radially protrudes from the outer peripheral s...  
WO/2017/133873A1
The invention relates to a gas turbine (1) having an axially adjustable rotor (2), comprising the following components: at least one external compressor air bleed (3) for bleeding compressor air; a control valve (4) for adjusting the amo...  
WO/2017/135187A1
This linear friction bonding device is for bonding, by frictional heat, a blade-side bonding surface of a blade and a disc-side bonding surface of a disc protrusion provided on the outer circumferential surface of a disc. The linear fric...  
WO/2017/129894A1
The invention relates to an assembly for a turbine engine (1), the assembly including: a casing (20) extending along a longitudinal axis (X-X') of the turbine engine (1), a surface heat exchanger (100) arranged along an inner edge (22) o...  
WO/2017/129518A1
A method for operating start-up of a compressor train is disclosed. The train comprises a driver machine (30) and at least a centrifugal compressor (1) drivingly coupled to the driver machine. The centrifugal compressor (1) in turn compr...  
WO/2017/129696A1
The present invention relates to a panel for machinery enclosure, particularly for turbomachine enclosures. More specifically, the present invention relates to a multilayered panel comprising several different layers (1, 2, 3, 4) each pe...  
WO/2017/126383A1
A gas turbine cooling system (50) is provided with a cooling air line (51) for guiding compressed air compressed in an air compressor (10) to high-temperature components, a cooler (63) for cooling the compressed air in the cooling air li...  
WO/2017/127068A1
An air turbine starter (ATS) assembly includes a rotatable pinion gear (72) wherein the rotatable pinion gear is coupled to a combustion engine (10), a speed sensor (78) measuring the rotational speed (302) of the rotatable pinion gear (...  
WO/2017/125427A1
The protection system comprises a screen assembly (100); the screen assembly (100) comprises a framework (110, 120, 160) with a connection part (150) for releasable mounting thereof, and one or more screen components (130, 140) releasabl...  
WO/2017/125178A1
The invention relates to a gas turbine (1) comprising a wet compression device (10) which allows droplets of an aqueous liquid mixture to be introduced into a compressor (2) of the gas turbine (1) during operation of the gas turbine (1),...  
WO/2017/125663A1
The invention relates to an aircraft turbomachine fan module (1) comprising: a fan (2), a low pressure compressor (3), inlet guide vanes (18) located upstream of the low pressure compressor and downstream of the fan (2), and a device for...  
WO/2017/123686A1
A gas turbine system includes a gas turbine engine, an exhaust processing system disposed downstream of and fluidly coupled to the gas turbine engine, and an air delivery system that may supply treated air to the gas turbine engine and t...  
WO/2017/123982A1
A catalytic ignition system (10) includes a gas fuel supply (12) and a catalytic igniter (14) that is in fluid communication with the gas fuel supply. The catalytic igniter comprises a metallic shell (18), a catalyst (20) disposed within...  
WO/2017/122468A1
A function-of-state acquisition unit acquires the function of state of a turbine. A time calculation unit calculates the time period of possible operation of a turbine in an over-firing operation, on the basis of the function of state an...  
WO/2017/122632A1
A blade pull-out device for pulling a blade out in a circumferential direction of a blade ring along a groove, the blade having been engaged in the groove which extends in the circumferential direction in the inner peripheral side of the...  
WO/2017/122469A1
A function-of-state acquisition unit acquires the function of state of a turbine, including turbine temperature. A variable calculation unit calculates past variables pertaining to the history of the function of state. A time calculation...  
WO/2017/120039A1
A fuel injector (600) for a gas turbine engine (100) is disclosed. The fuel injector (600) includes two primary tubes, a secondary tube (603), a primary gas gallery (643), and a secondary gas gallery (644). The two primary tubes are conn...  
WO/2017/120037A1
A center body assembly (700) for a fuel injector (600) is disclosed. The center body assembly (700) defines a primary liquid passage (721), a liquid gallery, swirl slots (775), and a prefilm passage (769). The primary liquid passage (721...  
WO/2017/119358A1
A removal device is provided with a base (101), a push bar (130), a bar movement mechanism (150), and a bar guide (140). The base (101) is restrained so as to be immovable in a first direction (Z). The push bar (130) can protrude to the ...  
WO/2017/120035A1
A fuel injector (600) for a gas turbine engine (100) is disclosed. The fuel injector (600) includes a flange assembly (610) with a distribution block (612), three main gas tubes, and an injector head (630). The distribution block (612) e...  
WO/2017/120038A1
A method for lean direct injection of a liquid fuel from a fuel injector (600) into a combustion chamber (390) of a gas turbine engine (100) is disclosed. The method includes injecting all of the liquid fuel into the combustion chamber (...  
WO/2017/116279A1
The invention relates to the field of aviation technology and is specifically intended for protecting gas turbine engines against dust and foreign objects entering same. Further applications exist in the automobile and industrial fields ...  
WO/2017/116112A1
The technical objective of the present invention is to provide an annular injection apparatus for wet compression, which allows injected droplets to evaporate as much as possible without being drained as a condensate, thereby being capab...  
WO/2017/115642A1
Before subjecting a turbine rotor blade to a heat treatment for removing residual stress, an adhesion cleaning step (scale cleaning step) is executed, wherein an ultrasonic cleaning process (steps S22, S25), in which the turbine rotor bl...  
WO/2017/115643A1
After a bonding coat layer removal step wherein a bonding coat layer (first coating layer) is removed by a chemical process, and a cleaning step wherein a turbine blade is cleaned by blast processing, an adhesion cleaning step (blast par...  
WO/2017/117371A1
A method includes compressing an air flow to a first pressure, transferring heat from the air flow to a liquefaction fluid via an intercooler heat exchanger, compressing the air flow to a second pressure greater than the first pressure, ...  
WO/2017/113258A1
A sealing cover (20) used for a gas turbine (100). The gas turbine (100) comprises at least one turbine disk (143), and the sealing cover (20) is used to cover the turbine disk (143). A side wall (22a) of the sealing cover (20) is provid...  
WO/2017/109330A1
The present invention relates to a multiflow turbojet engine comprising: a. an upstream fan (2) driven by a gas generator; b. the gas generator comprising first (3) and second (4) coaxial compressors; c. an intake case (8) forming a moun...  
WO/2017/110224A1
This sealing device is provided with: fins (54) extending from a stationary body (52) toward a rotating body (51) at a gap (53) between the stationary body (52) and the rotating body (51) without being in contact with the rotating body (...  
WO/2017/110448A1
A gas turbine cooling system (50) is provided with: a cooling air line (51) which guides air compressed by an air compressor (10) to a high-temperature component of a gas turbine (1); a cooler (64) which cools the compressed air; a flow ...  
WO/2017/108253A1
The invention relates to a power plant (1), comprising a compressor (2) for compressing combustion air (3), a combustion device (4), in which compressed combustion air (3) and a fuel (5) burn with each other, and a turbine (6), in which ...  
WO/2017/110971A1
This gas turbine engine (GE), which burns, in a combustion chamber (3), a compressed gas compressed by a compressor (1), and drives a turbine (5) by means of the obtained combustion gas, is provided with: a compressed gas supply part (17...  
WO/2017/109374A1
The invention relates to a turbomachine comprising an inter-flow compartment (110) extending radially between first and second intermediate walls, gas bypass ducts (102) passing through the second intermediate wall and communicating with...  
WO/2017/110955A1
A fuel injection device (1) for injecting a mixture of fuel and air into a combustion chamber (E) inside the combustor (CB) of a gas turbine engine, wherein the fuel injection device (1) is provided with a fuel injection valve (3) having...  
WO/2017/110973A1
A gas turbine engine (GT) provided with: a plurality of combustors (3) disposed at an incline toward the radially outward side from the turbine side toward the compressor side; and a diffuser inner tube (25) and outer tube (27) forming a...  
WO/2017/110104A1
The present invention reduces the thermal stress of flanges which join a combustor casing and a turbine casing together. This gas turbine (10) is provided with a compressor (14), a combustor (15), and a turbine (16) along the extension d...  
WO/2017/110465A1
A removal device is provided with a first member (110a), a second member (110b), and a separation mechanism (150). The first member (110a) is disposed between a first blade (40a) and a second blade (40b), which are adjacent to each other...  
WO/2017/109328A1
The present invention relates to a multi-flow turbojet engine comprising a. an upstream fan (2) driven by a gas generator, b. the gas generator comprising a first (3) and a second (4) compressor, which are coaxial, c. an inlet casing (8)...  
WO/2017/110039A1
The present invention is a turbine rotor disc repairing method for removing a defective part generated in an outer peripheral portion of a turbine rotor disc having a blade groove in the outer peripheral portion and for reforming the bla...  
WO/2017/109342A1
The invention relates to a power transmission mechanism (30) for a turbomachine (100) comprising: – a reduction gear (31) comprising a first gear (32) and a second gear (33) having different reduction ratios and each comprising a first...  
WO/2017/104705A1
According to the invention, a structural member containing an intermetallic compound is manufactured stably. The present manufacturing method is provided with: a mixed-layer forming step (S4) of forming a mixed layer by melting powder pa...  
WO/2017/098782A1
This fuel cell system is provided with: a fuel cell; an electric compressor that supplies a cathode gas to the fuel cell; a cathode exhaust gas passage through which flows a cathode exhaust gas discharged from the fuel cell; a turbine pr...  
WO/2017/098944A1
Provided are a seal fin, a seal structure, and a turbomachine in which an excellent leak-preventing effect can be achieved and leak loss in a turbomachine can be reduced. This seal fin (6) prevents fluid (SL) from leaking from a gap (Gd)...  
WO/2017/098452A1
This invention relates to a cooling system for an internal combustion engine, and is particularly suitable for cooling emission gases from electronically controlled, Tier 3 fuel injection engines [12] used in trackless mining machinery, ...  

Matches 1 - 50 out of 31,223