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Matches 1 - 50 out of 8,760

Document Document Title
WO/2017/213113A1
Corrosion resistance is enhanced while ensuring high enough heat shielding performance and erosion resistance. The present invention is provided with: a highly porous layer (6) that is formed on a heat-resistant substrate (100), that is ...  
WO/2017/203126A1
The present application describes a casing (10), in particular an exhaust casing, for a turbomachine, comprising an inner hub (14) having an axis (A) of rotation and an outer annular ferrule (16) extending around the hub (14), said ferru...  
WO/2017/203151A1
The present application concerns a method for manufacturing a casing (10'), in particular an exhaust casing, for a turbomachine, comprising the steps consisting of: a) producing casing sectors (30a), each casing sector (30a) comprising a...  
WO/2017/204941A1
The low pressure turbine includes a rotor, an outer casing, a plurality of stages of rotor blades, and a plurality of stages of stator vanes. The rotor includes a longitudinal centerline. The outer casing circumscribes the rotor. The plu...  
WO/2017/202400A1
The invention relates to a turbine casing (1) for a turbine (22), in particular a micro gas turbine (21), and to a turbine (22) having such a turbine casing (1). The turbine casing (1) comprises a support ring (2) and a ring contour comp...  
WO/2017/200644A1
An apparatus and method of cooling a rotatable member, in particular the rotor of a gas compressor forming part of a gas turbine, enclosed within a casing are provided. The gas compressor includes a rotor (234), a plurality of stages of ...  
WO/2017/200670A1
The present disclosure is directed to a shroud assembly for a gas turbine engine that includes a first shroud segment, a second shroud segment spaced from the first shroud segment, and a third shroud segment spaced from the first shroud ...  
WO/2017/195782A1
This stator blade (14) is disposed on an inner peripheral surface (11a) of a casing (11) which rotatably supports a rotor (12), and comprises a forward edge (21) which connects a tip surface (14a), which is supported on the inner periphe...  
WO/2017/194860A1
A turbine ring assembly comprises a plurality of ring sectors (10) made of a ceramic matrix composite material and forming a turbine ring and a ring support structure (3) comprising a first and a second annular flange (32, 36). Each ring...  
WO/2017/194865A1
Assembly (2) comprising an annular turbine distributor (3) for turbomachinery (1), an annular structural element (4) of the turbomachinery (1), coaxial with the distributor (3) and at least one device (5) for attaching the annular distri...  
WO/2017/194886A1
The present invention relates to a composite part comprising at least: - a fibrous reinforcement comprising silicon carbide fibers having an oxygen content of less than or equal to 1% as an atomic percentage, and - a matrix present in th...  
WO/2017/194237A1
The invention relates to a turbine for an exhaust gas turbocharger having a housing having two exhaust gas volutes, between which a separating wall is provided and which have a common waste-gate opening. The turbine housing is equipped w...  
WO/2017/190884A1
The invention relates to a turbine housing (21) for a turbocharger (1) of an internal combustion engine, comprising - an annular duct (22) for guiding an exhaust gas mass flow (AM) to a turbine wheel (12) that can be arranged in the turb...  
WO/2017/192147A1
A gas turbine engine has a flow metering device located between the combustor and the transition duct. The flow metering device engages the transition duct with a spring device. The flow metering device meters the airflow and axially cen...  
WO/2017/191075A2
A turbomachine component, such as a blade or a vane, is presented. The turbomachine component has an aerofoil. The aerofoil includes a suction side wall and a pressure side wall bordering an aerofoil cavity. The turbomachine component ha...  
WO/2017/190978A1
A gas turbine section with improved strut design A gas turbine section for an annular gas path is presented. The annular gas path is defined through a gas turbine engine. The gas turbine section includes an inner and an outer gas path wa...  
WO/2017/187093A1
The invention relates to a double-flow turbomachine (26) having an upstream fan wheel (36) and a downstream rectification unit (24) for an air outflow from a secondary annular air stream which is delimited radially on the inside by a rad...  
WO/2017/188040A1
The present invention reduces pressure loss in cooling air that is supplied to turbine stator blades. The present invention comprises: a cooling device (7) that generates cooling air by extracting and cooling compressed air (P) from a co...  
WO/2017/186481A1
The invention relates to a cooling fluid distributor for distributing cooling fluid in a cavity of a turbomachine blade, having at least two partial inserts (3, 5), wherein the partial inserts (3, 5) are introduced individually into the ...  
WO/2017/187091A1
To facilitate the removal of a bearing housed in an arm of a turbomachine casing, which bearing guides a transmission shaft of the turbomachine, the invention provides a casing arm (50) comprising a body (100) consisting of a vertical po...  
WO/2017/182423A1
The invention relates to a guide vane (1) for a fluid flow machine, in particular gas turbine, having an outer platform (2) in the properly mounted state of the guide vane, a vane leaf (6) projection from the outer platform (2), which ex...  
WO/2017/182322A1
Guide vane (1) for a turbomachine having, in the properly installed state, an outer platform (2), a blade airfoil (3) protruding from the outer platform, extending in a longitudinal direction and defining a cavity (4) in its interior, an...  
WO/2017/176186A1
The present invention relates to a turbine arrangement driven by exhaust gases from a combustion engine (2). The turbine arrangement comprises a turbine housing (7), a turbine wheel (6) rotatably arranged in the turbine housing (7), a fi...  
WO/2017/169537A1
A dehydrogenation processing method for turbine blades in a steam turbine, said method having a step in which heating steam is supplied to the steam turbine casing when a steam turbine plant is started up or is stopped, thereby heating t...  
WO/2017/168647A1
Provided is a fixed vane turbo charger, comprising: a housing including an impeller, an impeller housing space that houses the impeller, a scroll flow passage that is formed on the outer peripheral side of the impeller, and a communicati...  
WO/2017/164884A1
A gas turbine engine has an outer ring (15) formed by integrated exit pieces (10) and surrounds an inner ring (16). A seal section (20) having an L-shaped cross-section is positioned in a respective slot (11, 12) in the outer and inner r...  
WO/2017/164258A1
A structure for supporting turbine nozzles (13) and shrouds (21) opposing rotor blades adjacent to the nozzles by means of a turbine casing (23) covering a turbine (5) in a gas turbine. The front and back end parts of a circumferential f...  
WO/2017/158637A1
A turbine equipped with a cylindrical casing and turbine stator blades arranged along the circumferential direction in the interior of the casing, said turbine blades having: a blade effective section; a cooling medium flow path for circ...  
WO/2017/158264A1
The invention relates to a method for manufacturing a turbine shroud (24) for a turbomachine, involving manufacturing at least one turbine shroud segment (26), placing the turbine shroud segment (26) in a lower mold in such a way that an...  
WO/2017/158037A1
The repair member (200) comprises an inner platform portion (201) designed to replace part of the inner platform of a damaged vane, an outer platform portion (202) designed to replace part of the outer platform of a damaged vane, and an ...  
WO/2017/158266A1
The invention relates to a stator ring (20) of a flow path, preferably secondary, of a turbomachine (1), said ring (20) comprising: – an inner platform (52, 56) and an outer platform (54), – a plurality of stators (40) extending radi...  
WO/2017/155914A1
A ducting arrangement (30) in a combustion system of a gas turbine engine is provided. The ducting arrangement may be formed by duct segments (32) circumferentially adjoined with one another to form a flow duct structure (e.g., a flow-ac...  
WO/2017/154785A1
A flow path forming plate has formed therein a gas path surface (64p) in contact with combustion gas, an end surface formed at the peripheral edge of the gas path surface (64p), a first side through channel (90i), and a plurality of end ...  
WO/2017/154257A1
Tapered surface sections 21f, 22f are formed on inner-side surfaces of base sections 21a, 22a facing a flow path 14 at an outer band part 21 and an inner band part 22 of one of turbine stator blades 11, said turbine stator blades 11 bein...  
WO/2017/151146A1
An air cooled turbine stator vane with an impingement cooling insert (12,13) secured within a cavity, where a forward and an aft seal slot are formed between a backside surface of an airfoil and the impingement cooling insert in which fl...  
WO/2017/149414A1
The present invention relates to a method of manufacturing a bladed ring (9) for radial turbomachines, comprising the steps of : assembling a first support ring (15) with a second support ring (22), with a plurality of blades (27), with ...  
WO/2017/145623A1
An insert assembly (79) equipped with an insert (80), a reinforcing member (85), and a holding member (90). The insert (80) is affixed to one end of a blade main body (51) in the radial direction. The reinforcing member (85) is arranged ...  
WO/2017/144805A1
The invention relates to a rectifier (1) for an aircraft turbomachine compressor, the rectifier comprising an inner ferrule (24), an outer ferrule (26), and stator blades (28) secured to the inner and outer ferrules, the rectifier also c...  
WO/2017/145190A1
A steam turbine 90 according to the present invention is provided with: stator vanes 10 provided in a compartment 92 inside a casing through which steam flows from an upstream side toward a downstream side; and support means for supporti...  
WO/2017/140985A1
The invention relates to a turbine shroud sector (10) made of ceramic matrix composite material having a portion forming an annular base (12) with an inner surface intended for defining the inner surface of a turbine ring (1) when the sh...  
WO/2017/140986A1
The present invention relates to a method for manufacturing a part made of a ceramic matrix composite material, the method including at least the following step: infiltrating a fibrous preform with a molten composition including mostly s...  
WO/2017/134976A1
A method for implementing an abradable coating comprising: a pattern-forming step S1 in which, using a slurry containing ceramic particles and solvent, a slurry pattern is formed on the surface of a thermal barrier coating layer; and a f...  
WO/2017/129342A1
The invention relates to a continuous flow machine (2) having a rotor (4) that is mounted such that it can rotate about a rotational axis (6), and a diffuser (24) having a plurality of diffuser blades (28). So that the continuous flow ma...  
WO/2017/131650A1
A gas turbine engine has a transition duct assembly. Between two adjacent transition ducts (20) there is a transition side groove (23) that is formed by transition side rails (22). In this transition side groove (23) is inserted a side s...  
WO/2017/130144A1
The invention relates to equipment for implementing a method for depositing a vapor-phase metal coating onto turbine engine parts such as, for example, blades (14). Said equipment comprises at least one basket (2) defining a chamber (9),...  
WO/2017/127043A1
Turbine section (26) vane ring (44, 46) swallowing capacity, or throat cross section is selectively varied, through use of bi-cast vanes (50). The bi-cast vanes share a common, prefabricated vane airfoil profile (52), as well as subseque...  
WO/2017/127255A1
A transition duct system (10) for delivering hot-temperature gases from a plurality of combustors in a combustion turbine engine is provided. The system includes an exit piece (16) for each combustor. The exit piece may include a straigh...  
WO/2017/125289A1
An aerofoil (100) for a gas turbine (10) comprises: - an external surface (128) extending along a first axial direction between a leading edge (133) and a trailing edge (135) and extending along a second radial direction between a base (...  
WO/2017/126038A1
A stationary stator vane-type rotary machine is provided with: a rotating shaft; an impeller; an impeller housing having therein a scroll passage formed on the outer peripheral side of the impeller; a bearing housing connected to the imp...  
WO/2017/122632A1
A blade pull-out device for pulling a blade out in a circumferential direction of a blade ring along a groove, the blade having been engaged in the groove which extends in the circumferential direction in the inner peripheral side of the...  

Matches 1 - 50 out of 8,760