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Patent Searching and Data


Matches 1 - 50 out of 34,759

Document Document Title
WO/2019/116845A1
To protect the surface of a member exposed to a high-temperature environment and detect surface temperature or heat flow distribution, this magnetic thermoelectric conversion element, which is provided on the surface of a support in cont...  
WO/2019/116671A1
[Problem] To provide a fan blade, an engine, and an anti-icing/de-icing function-equipped structure with which it is possible to perform anti-icing and de-icing efficiently using a simple structure. [Solution] A fan blade 8 disposed on a...  
WO/2019/115964A1
The invention relates to a method (E) for detecting the ignition of a turbine engine combustion chamber, the method (E) comprising the steps of: receiving (E11) a first measurement of the exhaust gas temperature downstream from the combu...  
WO/2019/118129A1
A recuperator includes a monolithic heat exchanger core having a first side proximal to a combustor inlet and a turbine outlet, and a second side that includes an exhaust outlet. A compressed air inlet is located on the second side, and ...  
WO/2019/117135A1
A fuel supply device provided with: a first motorpump (10) that discharges fuel at a first flow rate toward an engine (X); a second motorpump (18) that discharges fuel at a second flow rate and merges this fuel with the fuel of the first...  
WO/2019/115939A1
Portion of a fluid drainage conduit (10) for a turbomachine, comprising an upstream section (12), a downstream section (16) that is fixed with respect to the upstream section (12) and a collecting chamber (20) into which the upstream sec...  
WO/2019/115121A1
The invention relates to a system and method for storing and recovering energy using compressed gas comprising at least one first and at least one second heat exchanger, a means for storing cold liquid and the means for storing hot liqui...  
WO/2019/115120A1
The invention relates to a method for storing and producing energy by means of compressed air, comprising the following steps: - compressing the air using staged compressors, during which time the air is cooled, after at least one compre...  
WO/2019/115119A1
The invention relates to a system and to a method for storing and harvesting energy using compressed gas, comprising at least one first and at least one second heat exchanger, a means for storing coid liquid and the means for storing hot...  
WO/2019/110939A1
The invention relates to a method for manufacturing an abradable coating, which consists of depositing, on a substrate surface (12), a filament of a thermosetting material, while ensuring both a relative movement between the substrate an...  
WO/2019/112649A1
A flight vehicle engine includes an isolator with a swept-back wedge to improve flow mixing. The wedge includes forward shock-anchoring locations, such as edges or rapidly-curved portions, that anchor oblique shocks in situations where t...  
WO/2019/110936A1
A method for in situ deposition of a coating on a turbomachine casing by additive manufacturing, consisting in depositing a filament (100, 200, 300, 400, 500, 600) of an abradable material on an inner surface of said turbomachine casing ...  
WO/2019/110940A1
The invention relates to an acoustic coating in an ordered array of interconnected microchannels, for receiving, on a receiving surface, an incident acoustic wave in a direction Ac normal to said surface, said method consisting in: depos...  
WO/2019/110958A1
A cover for an intake of an air-breathing engine in a missile is disclosed. The cover comprises a motive arrangement operable to move from a first configuration in which the cover is lockable to a missile, to a second configuration in wh...  
WO/2019/107392A1
The present invention comprises: a cylindrical combustion tube (21) through which a combustion gas (B) flows; an introduction pipe (41) connected to the outer peripheral surface of the combustion tube (21) such that one end of the introd...  
WO/2019/106299A1
The invention relates to an acoustic panel for an aircraft turbojet nacelle, of the type comprising an outer skin, an inner skin, and a cellular core (26) which is interposed between the outer skin and the inner skin and which comprises ...  
WO/2019/107474A1
A monitoring sensor for the state of a blade of a rotary machine, the monitoring sensor comprising: a sensor for monitoring the state of the blade of the rotary machine; a first section that is configured to be fixed to a casing of the r...  
WO/2019/107369A1
The present invention is provided with a downstream plate (59) that is provided on the downstream side of an upstream plate (58) and includes: an air introduction portion (86) to which cooling air from a cooling air introduction pipe (68...  
WO/2019/102556A1
Provided are a turbine blade (34) and a turbine, wherein the turbine blade (34) is effectively cooled to increase the efficiency of an electric power generation system. According to an embodiment, the turbine blade (34) has an inlet-side...  
WO/2019/100358A1
A gas turbine generator set, comprising a gas turbine, a power generating unit, and a transmission mechanism connected to the gas turbine and the power generating unit. Multiple high-speed direct-driven generators are connected to a larg...  
WO/2019/097905A1
This annular seal for a gas turbine is provided with: a first part extending in the circumferential direction on one end side in the axial direction and comprising a first groove opening on the one end side in the axial direction; and a ...  
WO/2019/098880A1
The invention relates to the field of operating aviation gas-turbine engines (GTEs) and can be used for controlling the feeding of fuel into manifolds of a main combustion chamber and/or afterburning combustion chamber of a gas-turbine e...  
WO/2019/098881A1
The invention relates to aircraft deicing systems. A method of controlling a deicing system on an air intake of an aircraft gas turbine engine consists in recording aircraft icing using a unit (1), transmitting icing data from the aircra...  
WO/2019/094726A1
An accelerated and/or redirected flow arrangement, optimally serving as a wildlife and/or debris excluder (WDE), is used in combination with a turbine-like device having an inlet end and an outlet end for fluid flowing therethrough, e.g....  
WO/2019/092189A1
Embodiments of the invention comprise a ball valve (100) for intended use in aircraft fuel systems comprising of an integrated valve housing (120), a ball housing portion (115), a ball member (112) housed rotatably within the ball housin...  
WO/2019/092929A1
A supercharger (1A) comprises a thrust disc (20), a stationary disc (30), a header tank (40), a lubrication oil supply channel (33), an air introduction tube (43), and a check valve (45). The lubrication oil supply channel (33) supplies ...  
WO/2019/092110A1
The subject matter of the invention is a method for monitoring the state of igniter plugs (1) of a jet engine. It is provided according to the invention that a measurement of the number of ignition sparks and/or the operating duration of...  
WO/2019/092910A1
Provided is a turbo fan engine (TF) provided with a power transmission device which switches main shafts (MS), connected to a starter/generator (SG) in a power-transmittable manner, between a state during starting and a state after start...  
WO/2019/093075A1
This turbine blade is provided with a blade body and a plurality of cooling passageways which extend in a blade height direction in the blade body and communicate with each other, forming a serpentine flow passageway. The cooling passage...  
WO/2019/094765A1
A system and method of an airflow control system for a vehicle is described herein. The airflow control system (100) includes an airflow housing (120) defining an airflow passageway (125) extending between a bypass opening (122) and an i...  
WO/2019/088107A1
Provided are a combustor and a combustion method with which it is possible to inhibit generation of nitrogen oxides. A combustor (10) provided with: a first wall (13A) forming a combustion chamber (12); a fuel injection nozzle (11) which...  
WO/2019/090232A1
A turbocharger (10) including a bearing housing (20), a shaft (40) mounted for rotation in the bearing housing (20), and a turbine wheel (34) attached to one end of the shaft (40) and configured to be driven by exhaust gas flow is disclo...  
WO/2019/088064A1
A method for producing a metal member comprising a first part (12) and a second part (14), which comprises: a first modeling step for modeling the first part (12) by powder bed type three-dimensional metal deposition modeling; and a seco...  
WO/2019/082642A1
The present invention reduces the amount of gas consumed when cooling gas by expanding the gas by using a plurality of expansion turbines. A high-pressure expansion turbine is equipped with a gas supply channel through which a bearing ga...  
WO/2019/082643A1
Provided is an expansion turbine which minimizes the amount of processing gas which leaks from a gap between a turbine impeller and a cover even when the pressure of the processing gas suddenly changes. The expansion turbine has a gas su...  
WO/2019/082880A1
A gas turbine combustor (3) is provided with: a nozzle (31A) in which an air ejection passage (F2) that extends along an axis (Ac) and that opens at a distal end thereof and a fuel supply passage (F1) that extends along the axis and that...  
WO/2019/082737A1
This axial-flow fluid machine is provided with: a holding ring (30) holding a stationary blade train; a casing (20) supporting the holding ring (30); and an eccentric pin (80). An engagement part (23) of the casing (20) has a protruding ...  
WO/2019/081916A1
An energy storage apparatus comprising: at least one inlet for incoming process gas; at least one outlet for expanded process gas; and a plurality of energy storage sub- systems configured to be arranged in series with each other and wit...  
WO/2019/081861A1
The invention relates to a retention device (101) for at least one cooling tube (120) of a cooling system (100) for a turbomachine case (10), the case (10) extending about an axial direction (X) of the turbomachine, the retention device ...  
WO/2019/082838A1
A shroud of this stator vane comprises a posterior passage (73n), an anterior passage (73p), and a plurality of rear-end passages (76). The plurality of rear-end passages (76) are arranged lined up in a lateral direction (Dc) between the...  
WO/2019/076519A1
The invention relates to an assembly for a turbine engine, comprising: an external housing (28) for a low-pressure compressor (4), referred to as a booster, having an annular wall (30); and an oil tank (46) having a circular internal cha...  
WO/2019/077251A1
Aircraft turbomachine (100) comprising a first channel (200) enabling communication between a high pressure compressor (30) and a high pressure turbine (50), a second channel (400) enabling communication between the high pressure compres...  
WO/2019/078309A1
The purpose of the present invention is to calculate the flow volume per unit time of fuel fed into a gas turbine, and to calculate the flow volume per unit time of air fed into the gas turbine. A turbine entry temperature is calculated ...  
WO/2019/074059A1
The present invention addresses the problem of providing: a heat-resistant titanium alloy member having high mechanical strength and high oxidation resistance at high temperatures, the titanium alloy member having low mechanical anisotro...  
WO/2019/073577A1
Provided is a service menu presentation system which: acquires operation data relating to an electric power generation plant; decides which operation pattern, from among a plurality of operation patterns set in advance in accordance with...  
WO/2019/075283A1
A thrust bearing assembly for a turbocharger includes a first thrust portion (50) disposed on a turbocharger shaft of the turbocharger, a second thrust portion ( 52) disposed on the turbocharger shaft and spaced axially from the first th...  
WO/2019/073167A1
The invention relates to thermal protection (18) comprising, superposed on one another in order, a metal plate, a first layer of insulating material, a layer of refractory fibres, and a second layer of insulating material, the metal plat...  
WO/2019/070160A1
The invention relates to a method of creating the required fuel pressure and flow rate in a fuel system of an aircraft gas turbine engine. According to the method, the operation of a fuel system and a gas turbine engine is supported by m...  
WO/2019/069011A1
The invention primarily relates to a discharge duct (30) of an intermediate housing hub for an aircraft turbojet engine, comprising an inlet end (41) and an outlet end (42), intended to ensure the passage of air from at least one dischar...  
WO/2019/070159A1
The invention relates to the field of aircraft engine manufacture, particularly to aircraft gas turbine engine oil system elements. A drive unit box comprises a gear, a nozzle, bearings, and a centrifugal impeller having blades. The cent...  

Matches 1 - 50 out of 34,759