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Matches 1 - 50 out of 30,873

Document Document Title
WO/2017/067982A1
Micro gas turbine unit (1) comprising a frame (2), a compressor part (3) provided with at least one compressor rotor (31), a turbine part (4) provided with at least one turbine rotor (41), which compressor rotor (31) and turbine rotor (4...  
WO/2017/068299A1
The invention relates to a supply system (10) for supplying a turbomachine with fluid. The supply system (10) comprises at least one centrifugal pump and a fluid recirculation branch (71). According to the invention, the fluid recirculat...  
WO/2017/069391A1
The present invention relates to a sealing assembly for a turbine, which may comprise: a first sealing member disposed at a stator of the turbine; and a second sealing member facing the first sealing member and disposed at a rotor of the...  
WO/2017/069201A1
In a compressor rotor shaft (21), a ventilation flow path (22) is formed which guides into the compressor rotor shaft a compressed gas flowing between two moving blade rows (51) which are adjacent in the axial direction (Da). The ventila...  
WO/2017/069145A1
In the present invention the end plate (60) of a blade (50) has a gas path surface (61) facing a combustion gas flow passage (49) side, an end surface (63) along the edge of the gas path surface (61), multiple passages (81p), and a baseb...  
WO/2017/069249A1
A ventilation flow path (22), a cooling air flow path (178), a mixing space (177) and a mixed air flow path (137) are formed in this gas turbine rotor (2). The ventilation flow path (22) guides compressed air (Acom) which is axially upst...  
WO/2017/067871A1
Disclosed herein is an integrated power generation and load driving system (1), comprising in combination: a multi- shaft gas turbine engine (3) comprising a high-pressure turbine (316) meĀ¬ chanically coupled to an air compressor (312);...  
WO/2017/069185A1
This blisk production method comprises an intermediate product formation step for forming a blisk intermediate product that has: a disk-corresponding part having a circular plate-like shape; a plurality of rotor vane-corresponding parts;...  
WO/2017/069922A1
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/2017/069582A1
The present invention relates to a sealing assembly for a turbine, the sealing assembly comprising: a first sealing member disposed on a fixed body of a turbine; and a second sealing member which faces the first sealing member and is dis...  
WO/2017/066223A1
A method and apparatus for starting and operating at least a first starter/generator (S/G) and a second S/G using at least one bi-directional converter and at least one of an AC power source and a first DC power source, including selecti...  
WO/2017/065574A1
Disclosed is a cooling apparatus for a gas turbine. A cooling apparatus for a gas turbine, according to an embodiment of the present invention, comprises: a compressor disk unit provided on the gas turbine and having a compressor disk co...  
WO/2017/066126A1
A device for altering infrared signature of an exhaust duct includes a housing configured to attach to an exhaust duct of a vehicle and at least one body attached to the housing at opposing ends of the at least one body, an opening in at...  
WO/2017/061433A1
Provided are a casing for a gas turbine and a gas turbine. The present invention comprises: a first casing (31) that is provided with a first flange section (42), a plurality of first connection holes (43), and a plurality of first cutaw...  
WO/2017/060584A1
The present invention relates to an aircraft comprising a fuselage (1), a propulsion unit (7) at the rear tip of the fuselage and at least two engines (3, 5) each driving an engine shaft (32, 52), the propulsion unit including at least o...  
WO/2017/060623A1
The present invention relates to an aircraft propulsion assembly comprising a turbine (15), at least one fan (10) and a mechanism for transmitting power between the turbine and the fan, characterized in that the power transmission mechan...  
WO/2017/061690A1
A device for removing foreign material of a gas turbine is disclosed. The device for removing foreign material of a gas turbine, according to one embodiment of the present invention, comprises: a combustor casing having a first cooling a...  
WO/2017/055223A1
A modular gas turbine system for on-shore LNG plants is disclosed. The module com- prises a base plate (3) having a top side (3T) and a bottom side (3B) and supports on the top side thereof at least a gas turbine engine (5), a control an...  
WO/2017/056997A1
This moving blade is provided with a blade body (2) in which a cooling flow passage (10) through which a cooling medium flows is formed. The blade body (2) includes: a top plate (4) forming an apex portion; and a thinning (6) which proje...  
WO/2017/055765A1
The invention relates to a device (10) for de-icing an air intake lip (12) of an aircraft turbojet engine nacelle (14), the device (10) comprising a de-icing circuit in which a heat transfer fluid (22) circulates, said heat transfer flui...  
WO/2017/056674A1
Provided is a low thermal expansion super-heat-resistant alloy which has low thermal expansion, high strength, good oxidation resistance and good creep rupture ductility, while being suitable for large-size components by being free from ...  
WO/2017/055766A1
The invention relates to a device (10) for de-icing an air intake lip (12) of an aircraft turbojet engine nacelle (14), the device (10) comprising a de-icing circuit in which a heat transfer fluid (22) circulates, said heat transfer flui...  
WO/2017/057992A1
The disclosed invention relates to a gas turbine tip gap control assembly comprising: a casing configured so as to guide a flow of combustion gas; a plurality of blades combining, in the casing, with a rotating shaft of a turbine; and a ...  
WO/2017/051111A1
The invention relates to a shock absorber assembly (200) for a non-streamlined blower comprising: an extension collar (210) having a first interface (201) suitable for being rigidly attached on a first module of the blower; a connector s...  
WO/2017/052795A2
Embodiments of the invention provide a system or a method for combusting reactants including a fuel and an oxidizer into combustion products in a combustor. A combustor can be configured to contain a flow of the reactants and the combust...  
WO/2017/050457A1
The invention is related to a support (1) for a machine part (10), particularly for a rotating machine part, more particularly for a gas turbine engine part, comprising a first support component (2), an interface component (4) comprising...  
WO/2017/052247A1
A device for cooling a gas turbine is disclosed. The objective of the device for cooling a gas turbine, according to one embodiment of the present invention, is to perform cooling by independently supplying cooling air to a plurality of ...  
WO/2017/051766A1
A gas turbine control device and method, a gas turbine control program, and a gas turbine, comprising: a first degree-of-opening setting unit (101) that sets a first inlet guide vane (IGV) degree-of-opening command value (S1) for inlet g...  
WO/2017/050670A1
Method and driveline used for stabilization of an electrical grid. The driveline for electricity generation comprises controllable power unit. Especially a gas motor or a gas turbine can be used as power unit. Further the driveline compr...  
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...  

Matches 1 - 50 out of 30,873