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Matches 1 - 50 out of 30,703

Document Document Title
WO/2017/048455A1
A turbine engine combustion system is disclosed including a fuel nozzle assembly having three independently controlled stages of water injection. A first stage includes water mixed with a gaseous fuel upon inlet to the nozzle, where the ...  
WO/2017/046499A1
The invention relates to a ventilation device for a turbomachine turbine casing, comprising a plurality of line sets (16') configured to spray air over the turbine casing, the line sets being arranged next to one another, each line set c...  
WO/2017/046942A1
[Problem] To provide a thermal barrier coating which can be used on a member in a system used under high-temperature, high-pressure conditions, such as a supercritical CO2 turbine, and is made of a highly durable ceramic. [Solution] A th...  
WO/2017/047502A1
A rotor blade (50) includes a blade path (71) that extends in the blade height direction (Dwh), a platform path (81) formed in a platform (60), and a linking path (75) that connects from the outer surface (93) of an axial mounting sectio...  
WO/2017/046481A1
The invention relates to a bowl (35) intended to supply oil to at least two oil-distribution circuits (43-44, 45-45a-45b) which are connected to a planet carrier (13) of an epicyclic reduction gearbox (10), the said planet carrier (13) r...  
WO/2017/046505A1
The invention relates to a drive gearbox (32) for turbomachine equipment, comprising a main shaft (34) intended to be rotationally connected to a power transmission shaft of a turbomachine, the main shaft (34) comprising at least one bev...  
WO/2017/047516A1
The objective is to enable the portion of a combustor tube where the temperature rises to be cooled efficiently, and to improve the reliability of a combustor tube without reducing the efficiency of a gas turbine. Therefore, this combust...  
WO/2017/042493A1
The invention relates to a particle-trapping device (2) for a turbomachine, said particles being contained in an air stream flowing inside a turbomachine, in particular the air stream flowing in the bypass region (17) of the combustion c...  
WO/2017/043157A1
This optical fiber probe is provided with: a probe main body 21; optical fibers 22 which are accommodated in an internal space S of the probe main body 21 and distal end portions of which are disposed on the side of the probe main body 2...  
WO/2017/043415A1
A seal member assembly structure and assembly method, a seal member, and a gas turbine, wherein, in a state in which a first flange portion (63, 65) of a combustor tail pipe 43 is fitted in a first fitting portion (73, 76) of a seal memb...  
WO/2017/038371A1
This gas turbine is provided with an exhaust diffuser (5) in which is formed an exhaust passage (Pe) for channeling exhaust gas from a turbine, and a cooling device (6) for cooling a structure in the exhaust diffuser (5) that faces the e...  
WO/2017/038086A1
An exhaust diffuser is provided with an inner cylinder, an outer cylinder that together with the inner cylinder forms an exhaust passage widening rearward from the front, and at least one tubular strut linking the inner cylinder and the ...  
WO/2017/041111A1
A chiller plant includes a first pump module (53) having at least one first pump module wall (65); a second pump module (55) having at least one second pump module wall; and a plurality of chiller modules (51) each having at least one ch...  
WO/2017/037399A1
The invention relates to a part (1) or an assembly of parts of a splitter stage of a turbofan, comprising a plurality of obstacles (4, 5, 6a, 6b) including at least one a blade (4) and at least one arm (5, 6a, 6b), and a platform (2) fro...  
WO/2017/033541A1
According to the present invention, an IGV opening command value is corrected to calculate an actual opening equivalent value which indicates an approximate value of an actual opening. A temperature estimation value, for a case where a m...  
WO/2017/033920A1
This turbine rotor blade (43a) is provided with a blade main body (51) and a tip shroud (52). The blade main body (51) is provided with a front edge-side cooling passage (64), a rear edge-side cooling passage (67), and an intermediate co...  
WO/2017/033726A1
A blade main body (51) of this gas turbine is provided with: a first cooling passage part (58); a second cooling passage part (59); a column part (60); and a plurality of protrusions. The first cooling passage part (58) is provided at th...  
WO/2017/031397A1
The invention relates generally to gas turbine engines used for electrical power generation. More specifically, embodiments of the present invention provide ways for improving gas turbine engine performance by reducing ice build-up on th...  
WO/2017/029007A1
The invention relates to a method for coupling a first sub-shaft, which has a first turbomachine and a generator connected to a mains supply, to a second sub-shaft, which has a second turbomachine, by means of an overrunning clutch, with...  
WO/2017/028316A1
A starting device (10) for a gas turbine is used for starting the gas turbine and comprises a stator (18) and a rotor (20) rotating relative to the stator (18). The rotor (20) comprises a rotating shaft (22) and a permanent magnet (24) f...  
WO/2017/027961A1
A bearing housing comprises a body having a partition wall delimiting the bearing housing from an environment and defining a bearing housing interior cavity configured to receive an oil feed. An inlet bore is in the partition wall in flu...  
WO/2017/028318A1
A starter-generator structure (10) for a gas turbine and the gas turbine. The starter-generator structure for a gas turbine comprises a stator (18) and a rotor (20) rotating relative to the stator (18). The rotor (20) comprises a rotatin...  
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 ...  
WO/2017/009278A1
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...  

Matches 1 - 50 out of 30,703