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Patent Searching and Data


Matches 1 - 50 out of 30,960

Document Document Title
WO/2017/104705A1
According to the invention, a structural member containing an intermetallic compound is manufactured stably. The present manufacturing method is provided with: a mixed-layer forming step (S4) of forming a mixed layer by melting powder pa...  
WO/2017/098782A1
This fuel cell system is provided with: a fuel cell; an electric compressor that supplies a cathode gas to the fuel cell; a cathode exhaust gas passage through which flows a cathode exhaust gas discharged from the fuel cell; a turbine pr...  
WO/2017/098944A1
Provided are a seal fin, a seal structure, and a turbomachine in which an excellent leak-preventing effect can be achieved and leak loss in a turbomachine can be reduced. This seal fin (6) prevents fluid (SL) from leaking from a gap (Gd)...  
WO/2017/098452A1
This invention relates to a cooling system for an internal combustion engine, and is particularly suitable for cooling emission gases from electronically controlled, Tier 3 fuel injection engines [12] used in trackless mining machinery, ...  
WO/2017/098124A1
The invention relates to a method for monitoring a start-up sequence of a turbomachine which comprises a compressor provided with a rotor, a starter capable of driving the rotor, and a combustion chamber. The start-up sequence comprises ...  
WO/2017/097294A1
The invention relates to a bearing assembly for a compressor of an internal combustion engine. The bearing assembly comprises an outer ring (3) having an outer cylindrical surface with a first and a second axial section (14, 15). The bea...  
WO/2017/098959A1
Provided are a seal structure, a turbomachine, and a method for producing a seal fin with which an excellent leak-preventing effect can be achieved and leak loss in a turbomachine can be reduced while suppressing an increase in productio...  
WO/2017/098960A1
Provided are a step seal, a seal structure, a turbomachine, and a method for producing a step seal with which an excellent leak-preventing effect can be achieved stably and leak loss in a turbomachine can be reduced stably. Disclosed is ...  
WO/2017/098932A1
A seal structure 30 of a steam turbine 1 which seals leak steam flowing through a gap between a rotor 12 and a casing 10 is provided with: a plurality of sealing fins 42 which are provided projecting toward the rotor 12 from a ring main ...  
WO/2017/098144A1
The invention relates to a hybrid power or thrust generator (100) including at least one thermodynamic turbine engine (20) and at least one electric power generator (40). An electric power generator (40) is electrically connected to at l...  
WO/2017/095690A1
A number of variations may include an outer race (12) having a first inner circumferential surface defining a first passage, a first inner race (18) defining a second passage and a second inner race (22) defining a third passage wherein ...  
WO/2017/094965A1
Disclosed is a device for diagnosing a combustion state of a gas turbine. The device for diagnosing a combustion state of a gas turbine according to the present invention comprises: a combustion diagnosis tube in which one end thereof is...  
WO/2017/093581A1
The invention relates to a lifting platform including a frame (10) formed at least by two main beams (11) and a cross-beam (12); at least four lifting device (30) for vertical movement disposed on said two main beams (11); at least four ...  
WO/2017/095569A1
A turbomachine complex includes at least one motor-generator, at least one power source coupled to the at least one motor-generator, and at least one load dissipative device coupled to the at least one motor-generator. The turbomachine c...  
WO/2017/096334A1
A process based on the combined use of yttrium and magnesium to inhibit vanadium corrosion of high temperature parts of thermal equipment. The combined use of yttrium and magnesium, applied in a variable yttrium/magnesium ratio, compared...  
WO/2017/090446A1
This method includes: carrying out refurbishment to reduce the amount of cooling air supplied to a turbine, and to replace at least some components provided in the turbine with components corresponding to the amount of cooling air suppli...  
WO/2017/089730A1
The invention relates to a turbomachine (24) of "open rotor" or turboprop type, comprising a nacelle (26) defining an air inlet (28), a central hub (30) and an annular air intake duct (32) surrounding the central hub (30) and opening int...  
WO/2017/090709A1
A gas turbine (1) is provided with a compressor (10), a turbine (30), a bleed line (61), and a component introducing line (66). The bleed line (61) extracts, as bleed air, compressed air from an intermediate compression stage (19a) of th...  
WO/2017/090221A1
According to the present invention, a transition structure between a combustor and a turbine in a gas turbine is provided with a transition piece including a duct and a flange projecting from a downstream edge of the duct, and a piece co...  
WO/2017/085386A1
The invention relates to a front part of an aircraft turbomachine (1) of the bypass type comprising a single fan (15), a gas generator (2) positioned downstream of the fan (15), a reducer (20) interposed between the gas generator (2) and...  
WO/2017/085430A1
The invention relates to a system (1, 100, 110) for supplying lubricating oil to members of a turbine engine having one reducer (9). The power supply system (1, 100) includes: a kinetic pumping device (2) to be connected upstream to an o...  
WO/2017/082219A1
In the present invention, an oscillating jig is provided with: an oscillating jig base that is connected to an oscillating table; a first clamp member that is provided to the oscillating jig base; a second clamp member that is provided i...  
WO/2017/080742A1
The invention relates to a method for assembling a turbomachine (TCO), wherein the turbomachine (TCO) has an outer case (OC), wherein the turbomachine (TCO) has an inner part (IP) for arranging in the outer case (OC), wherein the outer c...  
WO/2017/083684A1
The present invention is directed to methods and systems for utilizing supercritical carbon dioxide in an open thermodynamic cycle in which no compressors are used. In some embodiments, a method for utilizing supercritical carbon dioxide...  
WO/2017/077229A1
The reduction gear (6) comprises a pair of gearings (14, 15) mounted in parallel between two shafts (11, 12) and each equipped with an axially movable wheel (16, 17) for meshing (22, 23), by turns, with one of the shafts (11) and ensurin...  
WO/2017/077955A1
In a combustion cylinder, a gas turbine combustor, and a gas turbine according to the present invention: an outer-side region of a cooling part that is a region on the outer side relative to a reference line (L1) which runs through the c...  
WO/2017/079148A1
A gear pump comprising a bearing and first and second high pressure feeds from a bearing lube supply source to a lube pad disposed on an inside diameter of the bearing. Each of the first and second high pressure feeds includes an orifice...  
WO/2017/077801A1
A coating method for coating an engine compressor blade comprises: introducing a nitrogen-containing working gas in a chamber of an arc ion plating device; generating an electric discharge inside the chamber with a titanium aluminum allo...  
WO/2017/079309A1
A centrifugal pump includes a selectable regenerative style pumping element, including a regenerative pump rotor and at least one side wall flow channel formed by a rotating disc. The regenerative pumping element is selectable between a ...  
WO/2017/077219A1
The invention relates to an aircraft turbine engine module (10), comprising a degassing tube (14) and an ejection cone (12). The tube and the cone comprise centring means engaging together. The invention also relates to a locating and ad...  
WO/2017/078805A1
An aircraft engine guard, for protecting an aircraft engine against ingestion of large objects, includes a generally cone-shaped body, a base section of the rear end of the guard body and a dome section at the distal forward end of the g...  
WO/2017/077684A1
The variable stator blade control device controls the attachment angle of stator blades of an axial compressor, and is equipped with: arms which are fixed to the stator blades; rotary rings which are connected to one end of the arms and ...  
WO/2017/078122A1
In a turbine blade, a gas turbine, an intermediate product of the turbine blade, and a method of manufacturing the turbine blade according to the present invention, a blade body (51) having hollow shape, cavities (52, 53, 54) provided in...  
WO/2017/077921A1
A gas turbine startup method and device wherein a low-pressure bleed passage (41), a medium-pressure bleed passage (42), and a high-pressure bleed passage (43) for supplying compressed air bled from a low-pressure bleed chamber (25a), a ...  
WO/2017/075717A1
There is provided a hypersonic air-breathing engine having an air passage with an inlet, an outlet, and an air flow, and a turbojet between the inlet and the outlet. There is an air bypass around the turbojet, an afterburner downstream o...  
WO/2017/073544A1
This planning device has a remaining life specifying unit that specifies the remaining life of a component for a turbine. On the basis of the specified remaining life, a usage plan generating unit generates a usage plan that indicates th...  
WO/2017/073603A1
In this foil bearing, each of foils 12 is provided with: a top foil section 12A1 provided with a bearing surface X; and an under foil section 12B that is elastically deformable and that is arranged behind the top foil section. One end of...  
WO/2017/074221A1
The invention relates to engine design, and more particularly to gas turbine engines for aviation and terrestrial use. The present gas turbine engine comprises a high-pressure compressor, the straightening assembly (7) of which is dispos...  
WO/2017/074223A1
The inventions relate to drive structures of the driving units of a gas turbine engine. The present shaft assembly comprises an intermediate support, disposed inside an intermediate casing in the space between the main duct and the bypas...  
WO/2017/073554A1
This turbine analysis device has a state quantity acquiring unit that acquires state quantities for a turbine that include the temperature of the turbine. On the basis of the state quantities, a load specifying unit specifies a load hist...  
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...  

Matches 1 - 50 out of 30,960