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Matches 1 - 50 out of 35,083

Document Document Title
WO/2019/199851A1
A damped check valve (20) having multi-pressure operation is provided. The check valve includes a liner (22) with a poppet (24) movable within the liner. The liner defines a flow passage (38) aligned along a longitudinal axis (44) define...  
WO/2019/160575A3
A component (10) of a gas turbine engine is assembled or disassembled using induction heating. The induction heating is applied to the component (10) in order to create a sufficient temperature differential that permits the removal or pl...  
WO/2019/197743A1
The invention relates to a cooling device (21) extending circumferentially around a turbine engine casing (1), such as, for example, a turbine casing (7), comprising a support (24) extending axially and intended to be attached to the cas...  
WO/2019/198793A1
This valve opening degree determining device determines the valve opening degree of a cooling air adjustment valve for controlling the supply of cooling air to a disk cavity, the valve opening degree determining device being provided wit...  
WO/2019/197144A1
The invention relates to an axial turbomachine, in particular a turbofan for an aircraft. The turbomachine comprising a compressor, also referred to as a booster, with a rotor (12) and a stator, a turbine, a combustion chamber axially be...  
WO/2019/197773A1
An acoustic treatment panel (10) to be arranged on at least one wall of a turbojet engine (1) in contact with a fluid stream, the panel (10) comprising a first acoustically reflecting plate (14), a second plate (16), and a plurality of c...  
WO/2019/193274A1
In order to facilitate the filling of a lubricant tank (54), the invention relates to an aircraft engine assembly comprising a dual-flow turbine engine (1) and a pylon (2) for mounting the turbine engine, the assembly comprising thrust-a...  
WO/2019/193267A1
Cooling device (21) extending circumferentially around a turbomachine casing, such as a turbine casing, comprising a support (24) extending axially and designed to be secured to the casing, at least one cooling tube extending circumferen...  
WO/2019/190802A1
This disclosure provides a cross key anti rotation spacer for use in a gas turbine engine (100). A compressor disk assembly (220) can have a cross key ring (240) having a plurality of keys (241), teeth, or castellations, alternating with...  
WO/2019/187663A1
This heat shielding coating comprises: a bond coat layer that is layered on a parent material; and a ceramic layer that is layered on the bond coat layer, and includes a first layer with 10% to 15% porosity and a second layer with 0.5% t...  
WO/2019/185212A1
The invention relates to a ventilation device (1) for filtering air and for separating water aerosols out of the air. The ventilation device (1) has at least one filter element (3), at least one housing (4), at least one fan (5), and at ...  
WO/2019/187819A1
Provided is a blade manufacturing method by which a blade of a stable quality can be manufactured. The present invention involves: a shaping process in which a blade is molded by means of metal injection molding by injecting metal powder...  
WO/2019/188484A1
This fuel supply device is provided with a first supply pipe (2f), a first on-off valve (V1), a second on-off valve (V1, V2), a second supply pipe (2d), a connecting pipe (2h), a third on-off valve (V3), and a leak check measuring device...  
WO/2019/189355A1
A second outer surface (49ab) of a top plate (49) is recessed from a first outer surface (49aa) of the top plate (49) in the direction away from the inner peripheral surface (34a) of a turbine casing (34) so that a step (50) is formed be...  
WO/2019/188012A1
A combustion device (C) according to the present disclosure causes fuel to burn in a combustion chamber (N) using combustion air, and is provided with a reducing agent injecting portion (2e) which injects a reducing agent toward a flame ...  
WO/2019/187782A1
A fuel gas cooling system and a gas turbine plant are provided with: a gas cooler (39) which performs cooling by causing cooling water (CW) to come into contact with compressed fuel gas (FC) serving as a fuel gas; a cooling water dischar...  
WO/2019/187559A1
Provided is a combustor wherein flashback can be sufficiently suppressed while reducing NOx. This combustor comprises: a casing 20 having in the interior thereof an air chamber 121 filled with air; mixed flow path formation members 131, ...  
WO/2019/187435A1
This gas turbine for an aircraft comprises: a moving blade (24) having a moving blade body (41) extending diametrally outward from a rotor that rotates about an axis, and a fin (43) protruding from an outer peripheral surface (42a) of a ...  
WO/2019/188588A1
This turbine rotor blade is provided with a blade body including a belly-side blade wall and a back-side blade wall. The blade body includes; a serpentine flow passage comprising a cooling flow passage divided into a plurality of portion...  
WO/2019/185364A2
The invention relates to a ventilation device (1) for filtering air and for separating water aerosols from air. The ventilation device (1) has at least one filter element (3), at least one housing (4), at least one fan (5) and at least o...  
WO/2019/185666A1
The present invention relates to a generator comprising a rotor, an inner shaft, an outer shaft, and an actuation means. The outer shaft is connected to the rotor so as to transfer a torque to or from the rotor. The inner shaft is at lea...  
WO/2019/190477A1
A sealing arrangement (10) in a gas turbine engine to seal a gap between first and second turbine components (12, 14) is provided. The sealing arrangement includes a first arcuate feather seal (16) connected to an anchoring assembly (18)...  
WO/2019/181188A1
This fuel nozzle for a gas turbine comprises: a nozzle body; a fuel injection opening formed in the nozzle body so as to have, on a one-end side, an injection port that opens in the outer surface of the nozzle body; and a fuel channel pr...  
WO/2019/183426A1
An internal combustion engine for an aircraft includes a crankshaft configured to drive a driven element; a camshaft coupled to the crankshaft; and an ignition controller coupled to the camshaft and including a visual indicator, the visu...  
WO/2019/181256A1
An intake air cooling device (1) has an intake air duct (2) that is disposed on the intake air side of a gas turbine and is provided therein with a spray nozzle (7). The intake air duct (2) has: an intake air opening (3) in which a filte...  
WO/2019/179993A1
There is provided a casing assembly for a gas turbine engine comprising: a casing and electrically conductive intumescent material extending around the casing. The intumescent material is being activatable in response to electrical curre...  
WO/2019/175572A1
Disclosed is an electric vehicle with an architecture suitable for an electro- hydraulic propulsion that decouples the drive to allow greater freedom in the location of the major components for different types of vehicles and achieve opt...  
WO/2019/171000A1
The invention relates to an active device for attenuating acoustic emissions (8) from a turbojet of an aircraft, characterised in that the device comprises conduits (20) for the circulation of a pressurised air flow supplying rotating el...  
WO/2019/170278A1
The invention relates to a radial bearing for an exhaust-gas turbocharger, wherein the radial bearing is designed as a plain bearing and comprises a bearing bushing (6) that is designed so as to be able to accommodate a shaft (3) of the ...  
WO/2019/172020A1
Provided are: a leading edge cover member suitable for use, as a countermeasure against water droplet erosion, for example, in a composite-material blade body used in an industrial gas turbine compressor; a leading edge cover member unit...  
WO/2019/172221A1
This heat exchanger (100) for an aircraft engine is provided with a core section (1) and a heat radiation fin (2). The heat radiation fin is formed so that the ratio y/Y of the height y from the surface (10) of the core section to the po...  
WO/2019/172372A1
Provided is a fuel supply control device (F, F1) in which a parallel flow passageway of an orifice (8) and a pressurizing valve (7) is used as a complex pressurizing valve for a fuel supply amount, and which controls a fuel supply pump (...  
WO/2019/171605A1
This heat exchanger system (100) is provided with a heat exchanger (1) and a valve (20). The valve connects an external inlet (2a) and a supply port (2c), and is configured to be capable of switching between a first state (P1) in which a...  
WO/2019/166040A1
Disclosed is a method for reducing contrails during operation of an aircraft (100, 100') having a heat engine (10). The method comprises: bringing about condensation of the moisture contained in the exhaust gas (A) of the heat engine by ...  
WO/2019/167276A1
Provided are a fuel gas storage system for a gas turbine and a method for supplying fuel gas to the gas turbine, wherein the system comprises: a storage tank (41) that stores fuel gas; a flow line (L12) through which the fuel gas stored ...  
WO/2018/164149A8
This cooling structure for a turbine airfoil (1) is provided with: a cooling passage (17) formed between a first blade wall (3) that is curved in a concave shape with respect to a high-temperature gas flow passage (GP) and a second blade...  
WO/2019/168174A1
A thermal barrier coating which comprises a metal bonding layer that is formed of an alloy containing Al, a thermal barrier layer, and an intermediate layer that is arranged between the metal bonding layer and the thermal barrier layer. ...  
WO/2019/166703A1
An electrical generator (9) is housed in an annular cavity (14) between the casing (15) and the propeller shaft (3) of a turboprop, while imposing little or no additional space requirement and with lightweight ancillary equipment (16) an...  
WO/2018/164150A8
This cooling structure for a turbine airfoil (1) is provided with: a cooling passage (17) formed between a first blade wall (3) that is curved in a concave shape with respect to a high-temperature gas flow passage (GP) and a second blade...  
WO/2018/164148A8
This cooling structure for a turbine airfoil (1) is provided with a lattice structure (23) formed by a first rib pair (33A) and a second rib pair (33B) which are disposed in a cooling passage (17) and overlap each other in a lattice shap...  
WO/2019/162601A1
The invention relates to an aircraft turbine engine (10) having a primary air flow path (16) in which a low-pressure compressor (30) and a high-pressure compressor (32) are arranged, a secondary air flow path (20) which is located around...  
WO/2019/162600A1
The invention relates to an aircraft turbine engine (10) comprising a primary air flow path (16) in which a low-pressure compressor (30) and a high-pressure compressor (32) are arranged, a secondary air flow path (20) comprising a plural...  
WO/2019/162610A1
The invention relates to a propulsion unit comprising a nacelle and a turbofan engine, comprising a thrust reverser having gratings provided with movable thrust reversal gratings arranged around an annular duct for fresh air from the tur...  
WO/2019/158451A1
An acoustic damper (100) for a gas duct system (20), comprises a housing (1) comprising a first wall (2) and a second wall (3) opposite to and spaced from the first wall (2) so as to at least partly define a housing volume there between....  
WO/2019/158884A1
The invention relates to a nacelle for a turbomachine, the nacelle comprising an inner wall that is annular about a longitudinal axis of the nacelle, the annular inner wall being designed to surround at least part of the turbomachine, th...  
WO/2019/158876A1
The invention relates to a profiled air flow structure comprising a body (62) and acoustically absorbent porous regions (52), having an upstream, a downstream, a leading edge (164) upstream and/or a profiled trailing edge downstream, and...  
WO/2019/158883A1
The invention concerns an assembly (42) for retaining an epicyclic gear train in a turbomachine, comprising an annular casing (50) in which a first annular part (44) and a second annular part (46) are engaged, prevented from rotating in ...  
WO/2019/158877A1
This relates to a turbomachine with a front-mounted fan, comprising an annular flow-splitting wall (160) provided a nose (16), for splitting an incoming air flow between a primary flow and a secondary flow, the nose having a leading edge...  
WO/2019/158875A1
An aircraft turbine engine comprises an annular wall (160) for splitting a flow of air, downstream of an upstream fan (14), first stationary blades (24) for guiding a primary flow and the second stationary guidance blades (26) attached t...  
WO/2019/158854A1
The invention concerns an outer shroud (16) of an intermediate casing for a dual flow turbine engine for an aircraft, the shroud comprising: - an annular downstream portion (24) provided with a shroud opening (30) passing through an annu...  

Matches 1 - 50 out of 35,083