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Matches 1 - 50 out of 30,531

Document Document Title
WO/2017/026314A1
A shroud of a stationary blade (50) has formed therein a plurality of circumferential ejection passages (95) that connect with a cavity (69) into which cooling air (Ac) flows and that open on a circumferential end surface (63). Of a cent...  
WO/2017/024390A1
An auxiliary power unit for an aircraft, including an internal combustion engine having a liquid coolant system, a generator drivingly engaged to the internal combustion engine and having a liquid coolant system distinct from the liquid ...  
WO/2017/024393A1
A turboprop engine assembly for an aircraft, including an internal combustion engine having a liquid coolant system, an air duct in fluid communication with an environment of the aircraft, a heat exchanger received within the air duct ha...  
WO/2017/025774A1
The invention is applicable to industrial gas turbines, and looking into reducing load consumed by gas turbine COMPRESSOR, and maximizing turbine MASS FLOW. For invention implementation, High-pressure water injection system is to be intr...  
WO/2017/022214A1
A cooling mechanism for a gear is provided with: a gear comprising a plurality of teeth that extend in a specific direction; and a nozzle that sprays oil toward the tooth surfaces of the gear. The nozzle extends in a specific direction a...  
WO/2017/022397A1
A gas turbine fuel flow rate setting device (100) is provided with a flow rate ratio computing unit (160) and a flow rate computing unit (180). The flow rate ratio computing unit (160) accepts a parameter (CLCSO) correlated to the gas tu...  
WO/2017/021621A1
The invention concerns a method for isolating a tank (21) of combustible fluid from a downstream portion (23) of a fluid supply system for a turbine engine. The supply system (20) comprises the tank (21) and a cutoff valve (22) located b...  
WO/2017/022400A1
An air turbine drive spindle (100) with which it is possible to suppress a deterioration in painting quality by suppressing the inflow of a driving gas into a through-hole in a rotating shaft is provided with a housing and a rotating sha...  
WO/2017/023559A1
An anti-ice valve, a turbine engine including an anti-ice valve assembly and a method of operating an anti-ice valve where an anti-ice valve has a housing and a valve element configured to control a flow of hot bleed air through the hous...  
WO/2017/017369A1
The invention relates to a method for producing an acoustic attenuation panel comprising two outer skins (4, 6) made from a composite material with a ceramic matrix containing a fibrous reinforcement, said skins being assembled on each s...  
WO/2017/018154A1
A water feeding system (50) is provided with: a first water feeding line (51) through which first feed water flows; a second water feeding line (52) through which second feed water having a lower pressure than the first feed water flows;...  
WO/2017/017392A1
The proposed invention is an air-flow straightening assembly for a turbine engine comprising: - a cylindrical platform (15) centred on an axis (X-X), - at least one straightener blade (20) extending from the platform, - a structural arm ...  
WO/2017/015746A1
A mid-turbine frame module comprises an outer structural ring, an inner structural ring and a plurality of circumferentially spaced-apart spokes structurally interconnecting the inner structural ring to the outer structural ring. At leas...  
WO/2017/017378A1
The invention concerns an anti-icing system for a turbine engine blade (A1) extending between an outer housing (CE) and an inner housing (CI) delimiting a flow path (VN), characterised in that it comprises means for injecting a jet of ai...  
WO/2017/017367A1
The invention relates to a method for producing an acoustic attenuation panel from a composite material with a ceramic oxide matrix, comprising the following steps: a) draping a plurality of plies in a mould, said plies consisting of fib...  
WO/2017/015745A1
A mid-turbine frame of a gas turbine engine has a structural ring assembly comprising an outer ring, an inner ring having a plurality of threaded bosses extending from a radially outer surface thereof, and a corresponding number of struc...  
WO/2017/015747A1
A mid-turbine frame module comprises an outer structural ring, an inner structural ring and a plurality of circumferentially spaced-apart spokes structurally interconnecting the inner structural ring to the outer structural ring. The spo...  
WO/2017/017708A1
Provided is a cobalt-base alloy member having improved oxidation resistance at high temperature. This method for producing a cobalt-base alloy member includes a step for preparing a cobalt-base alloy on which an aluminizing treatment has...  
WO/2017/017368A1
The invention relates to a porous body (9) made from a ceramic-matrix composite material and intended for an acoustic attenuation panel, comprising: a plurality of interwoven ceramic fibres (13), a metal oxide matrix (15), and a pluralit...  
WO/2017/015341A1
A control system for an in-flight engine restart system of a rotorcraft includes an engine control unit that controls and detects status of an engine. The control system also includes a flight control computer that communicates with the ...  
WO/2017/015343A1
A system and related method for providing a highly reactive fuel to a combustor of a gas turbine are disclosed herein. The system includes a fuel supply system that is in fluid communication with a fuel supply. The fuel supply system inc...  
WO/2017/013347A1
The invention relates to a fuel metering device (12-1) comprising a mobile element (22) comprising at least one fuel passage section (32) opening upstream toward a fuel supply duct and opening downstream toward a usage duct via a meterin...  
WO2017010627A1
The present invention relates to a gas turbine that includes a cooling system provided with a cool-air supply path detouring to an outer casing and, more specifically, to a gas turbine that includes a cooling system and a cooling method ...  
WO2017009278A1
The invention discloses a silencing unit (12) for use in a gas turbomachinery (1) for reducing the noise generated by the gas turbomachinery (1). The silencing units (12) are disposable between an air supply unit (4) and a blower (6). Th...  
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/2017/007809A3
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/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/2016/207828A3
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/2016/207829A1
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...  

Matches 1 - 50 out of 30,531