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Patent Searching and Data


Matches 151 - 200 out of 21,942

Document Document Title
WO/2017/192247A1
A metal leading edge includes a nose positioned along the leading edge of a fan blade airfoil body. The metal leading edge also includes a first edge extending axially aftward from the nose along a pressure side of the fan blade airfoil ...  
WO/2017/191071A1
A system for cooling a blade (38) in a rotor (22) of a gas turbine (10), the blade (38) comprising: - a root (122) for connecting the blade (38) to the rotor (22), - an aerofoil (126) connected to the root (122), - a cooling passage exte...  
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/2017/191075A2
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/2017/186492A1
The invention relates to a method for profiling blades of an axial turbomachine, having the steps of: a) preparing a geometric model of a blade profile (R, -1, +1); b) determining an oscillation mode of the geometric model; c) calculatin...  
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/2017/189291A1
The present disclosure relates to a turbine wheel for a turbine of an exhaust gas turbocharger. The turbine wheel has a base body comprising a back wall and a plurality of turbine blades, connected to the base body, which each comprise a...  
WO/2017/189208A1
A gas turbine engine blade (10), including a base portion (12) having a cast wall, and a tip portion (14) attached to the base portion and having a wall (60) formed by an additive manufacturing process. The tip portion wall may be formed...  
WO/2017/186661A1
The present invention provides a gas turbine blade and a gas turbine, the gas turbine blade comprising: a blade profile, with a gas cooling channel provided in the blade profile; and a top sealing cover, disposed at the top of the blade ...  
WO/2017/188991A1
A staged cooling system for turbine component (10) includes a near-wall cooling channel (80) defined between an outer wall (12) of the turbine component (10) and a hollow core (30) positioned in an internal cavity (24) of the turbine com...  
WO/2017/186640A1
The invention relates in general to rotor blades and/or guide blades for a blading, that is to say the blades of a compressor or of a turbine. The invention also relates to a method for producing such a rotor blade or guide blade. The in...  
WO/2017/187050A1
A method for producing a part from composite material comprises positioning a fibrous texture (10) in a mould (110) comprising, in the lower portion of same, a part made from porous material (130) on which a first face (10b) of the textu...  
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/2017/184138A1
A preloaded snubber assembly for turbine blades includes a plurality of turbine blade airfoils (10) including a trailing edge and a leading edge joined by a pressure side and a suction side to provide an outer surface (14) extending in a...  
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/2017/180100A1
A gas turbine engine component (100) formed of material having phononic regions (30). The phononic regions (30) are formed of alloys or allotropes of the material (20). The phononic regions (30) modify the behavior of the phonons (10) an...  
WO/2017/180102A1
A gas turbine engine component (100) formed of material (20) having phononic regions (30). The phononic regions are formed of non-metallic nanostructures (35). The phononic regions (30) modify the behavior of the phonons (10) and control...  
WO/2017/180101A1
A gas turbine engine component (100) formed of material having phononic regions (30). The phononic regions (30) are formed of doped nanostructures (35). The phononic regions (35) modify the behavior of the phonons (10) and control heat c...  
WO/2017/179711A1
A steam turbine rotor blade equipped with an extension part (7) that is provided at the tip-end portion in the blade height direction of a blade main body (61) on which a front edge part (61a) is formed, and that extends from a negative-...  
WO/2017/178747A1
The invention relates to a blade (16), in particular a fan blade, for resurfacing an abradable coating (26) on an internal surface of a turbine engine case (18) intended to surround the blade. The comprises a root (20) and an airfoil (24...  
WO/2017/180104A1
A gas turbine engine component (100) formed of material (20) having phononic regions (30). The phononic regions (30) are formed of void nanostructures. The phononic regions (30) modify the behavior of the phonons (10) and manage heat con...  
WO/2017/180117A1
There is provided a component (30) formed from a plurality of laminates (10, 32) stacked on one another, thereby defining a stacked laminate structure (25) having a leading edge (18) and a trailing edge (20). Each of the plurality of lam...  
WO/2017/180105A1
A gas turbine engine component (100) formed of material having phononic regions (30). The phononic regions (30) are formed of anisotropic nanostructures (35) that are oriented in different directions than the bulk of the material forming...  
WO/2017/176723A1
A turbine blade (10) includes a platform (12) with an internal cavity (13) formed therein and an airfoil (14) extending radially from the platform. The turbine blade includes a first portion (20) made from ceramic matrix composite materi...  
WO/2017/174355A1
The invention relates to a rotor disk assembly having a rotor disk (01), on which a plurality of sealing plates (11) is arranged in front of an end side (02) and wherein a plurality of separate sealing vanes (21) are arranged radially ou...  
WO/2017/175563A1
Provided are a nickel-base alloy having high high-temperature strength, a turbine blade using same, and a method for producing an injection molded article of the nickel-base alloy. The nickel-base alloy (10) contains: at least one metal ...  
WO/2017/174723A1
The invention relates to a seal on a rotor disk assembly having a rotor disk (01), which rotor disk (01) has a plurality of axially extending blade-retaining grooves (09) distributed on the outer periphery. Furthermore, the rotor disk as...  
WO/2017/168335A1
The present invention concerns a method for the construction of bladed discs for radial turbomachines, comprising: preparing a disc (6, 14) provided with a front face (7); preparing a plurality of reinforcement rings (23) with different ...  
WO/2017/168766A1
A rotary machine blade (31) equipped with a clearance flow suppression blade section (34), the lean angle of which has one or more inflection points, and which is formed such that when the direction from a positive-pressure surface (31a)...  
WO/2017/171764A1
An airfoil (10) includes at least one internal cooling channel (A-F) extending in the radial direction and adjoined on opposite sides by an airfoil pressure sidewall (16) and an airfoil suction sidewall (18). An internal surface (16a) of...  
WO/2017/168777A1
Provided is a turbine blade designing method for designing a turbine blade, wherein: correlation data associating heating temperature range, creep strength, and crystal grain size is prepared in advance; and the method is provided with a...  
WO/2017/167578A1
A method for manufacturing a number of gas turbine components is described. The method comprises the steps of: selecting (60) material for manufacturing a number of components (38), making at least one coupon (61) of the material for tes...  
WO/2017/168334A1
The present invention relates to a radial turbomachine with axial thrust compensation, comprising: a fixed casing (3); a plurality of main concentric bladed rings (9',9",9"',9"") arranged in the fixed casing (3) around a central axis (X-...  
WO/2017/167615A1
The invention relates to a turbine blade (100) comprising: a blade tip, a cooling structure (10) comprising cooling channels (5) which are designed to have cooling fluid passed through them in order to cool the turbine blade (100) during...  
WO/2017/167412A1
The invention relates to a structure (A) and to a method for positioning and fastening a tool, which can be fastened to the structure to an elongated recess, in particular groove (N), in particular of a rotor, that is spatially extending...  
WO/2017/171763A1
A turbine airfoil (10) includes a flow blocking body (26) positioned an internal cavity (40). A first near-wall cooling channel (72) is defined between the flow blocking body (26) and an airfoil pressure sidewall (16). A second near-wall...  
WO/2017/162411A1
The invention relates to a method for treating a component (1) which is provided with a thermal barrier coating (4), wherein a non-metallic protective layer (5) comprising at least one oxidizable constituent is applied at least on areas ...  
WO/2017/165631A1
This invention is directed to a centrifuge rotor, such as for use in a disc nozzle centrifuge, having a bowl including an improved positioning and orientation of discharge nozzles for facilitating tangential flow of fluid discharged ther...  
WO/2017/161952A1
Provided is a new-type turbine, comprising a shaft (1), several turbine units (4) and a cylindrical housing (3), wherein the turbine units (4) are arranged in parallel and are mounted on the shaft (1); a closed cavity is provided inside ...  
WO/2017/164935A1
A turbine airfoil (10) includes a trailing edge coolant cavity (41f) located in an airfoil interior (11) between a pressure sidewall (14) and a suction sidewall (16). The trailing edge coolant cavity (41f) is positioned adjacent to a tra...  
WO/2017/162365A1
Damping vibrations in a gas turbine It is described an arrangement (60) for damping vibrations in a gas turbine (10), comprising: a rotor shaft (22) arranged for rotating; a first rotor component (62) connected to the rotor shaft (22); a...  
WO/2017/162964A1
The invention relates to an aircraft turbomachine comprising at least one unducted propeller having a plurality of blades (6), each blade (6) comprising: a blade body (8) made of a composite material with a fibrous reinforcement densifie...  
WO/2017/162743A1
The invention relates to a film cooling hole (20) of gas turbine components to be cooled, having an inflow section (26) with a constant flow area, to which a diffuser section (28) with a variable flow area is connected. The aim of the in...  
WO/2017/163911A1
This rotary machine (100) is equipped with: a rotor (1) on the outer circumferential surface (1S) of which recesses (8) are formed; stator blades (7) each having a stator blade body (70) extending from the outside toward the inside in th...  
WO/2017/160475A1
A method of manufacturing a gas turbine engine component (10) and the component so formed. The method includes: stacking a plurality of CMC layers (16) along a metal core (30) to form a stack of disconnected CMC layers, wherein adjacent ...  
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/2017/157956A1
The present technique presents an aerofoil for a gas turbine, a compressor having the aerofoil, a method for designing the aerofoil, and a method for manufacturing the aerofoil. The aerofoil extends from a platform and includes a concave...  
WO/2017/158304A1
The invention relates to a rotor (3) of a member (7) of a turbomachine (1), for example a rotor of a turbine (7), said rotor (3) comprising: – a first element (30), – a second element (20) defining with the first element a ventilatio...  
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...  

Matches 151 - 200 out of 21,942