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Matches 1 - 50 out of 21,429

Document Document Title
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...  
WO/2017/153687A1
The invention relates to a turbomachine turbine vane comprising a root having a blade (12) comprising a leading edge (16) and a trailing edge (17) and a lower surface wall (14) and an upper surface wall (13), as well as: a manifold for c...  
WO/2017/153219A1
The invention relates to a rotor blade for a gas turbine, comprising a blade (1) extending in a radial direction, with a blade body (2) comprising a periperal wall with a pressure-side wall section (3a) and a suction-side wall section (3...  
WO/2017/152995A1
A device (1) for re-contouring gas turbine blades (2) in the installed state, comprising a holding device (3) with at least one chip-removing tool (4), and a guide device (5) for guiding the chip-removing tool (4) along a leading edge (6...  
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/2017/154852A1
In this turbine rotor blade assembly 1, turbine rotor blades 10 are equipped with: a platform 11 having a blade root 12 secured to a turbine disk 30; a profile 13 rising from the platform 11; and a shroud 14 provided on the tip end of th...  
WO/2017/155506A1
A turbine of a gas turbine engine with a rotor (11) and a stator (15, 16) forming a rim cavity (18), where the rotor includes a turbine rotor blade (12) with a cooling air channel opening into the rim cavity (18), and a centrifugal impel...  
WO/2017/154809A1
The present invention provides a first generation Ni-based unidirectionally solidifed alloy that contains neither Co nor Re. This Ni-based unidirectionally solidified alloy has excellent TMF properties, excellent creep properties, and an...  
WO/2017/152849A1
Disclosed are a method and device for generating a hydrodynamic force with a spiral body. The device comprises the spiral body which is of a spiral structure or a helical structure. On the basis of fluid, with the fluid as a core and an ...  
WO/2017/153573A1
An alloy is disclosed, encompassing reduced amounts of Hafnium and Carbon so as to achieve an excellent oxidation resistance, as well as gas turbine applications using the same.  
WO/2017/152891A1
The invention relates to an adhesion promoter layer for joining a high-temperature protection layer to a substrate, which adhesion promoter layer is characterized in that the adhesion promoter layer comprises a first layer of an adhesion...  
WO/2017/155497A1
A turbine blade (10) includes an airfoil (12) extending span-wise along a radial direction (Ra) relative to a turbine axis having a leading edge (14) and a trailing edge (16) joined by a pressures side (18) and a suction side (20), a tip...  
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/2017/148891A1
In a gas turbine system (10) having a turbine (12) which can be impinged on by hot gas and which has a turbine wheel (18), having a combustion chamber (14) for generating hot gas for the turbine (12) and having a compressor (24) with a c...  
WO/2017/148916A1
The spallation behavior of a TBC is significantly improved by means of a special recess around cooling air holes (11`, 11``,...), in which an enveloping recess (13`, 13``) and a strip-shaped depression (8), which connects the enveloping ...  
WO/2017/149400A1
The present invention relates to a method for the construction of bladed rings for radial turbomachines, comprising: preparing an annular block (31 ); roughing the annular block (31 ) by removing material to define a first axial section ...  
WO/2017/148630A1
The invention relates to a rotor (01) for use in a gas turbine, comprising a plurality of compressor segments (21), a plurality of central segments (31), and a plurality of turbine segments (41); the compressor segments (21) and the turb...  

Matches 1 - 50 out of 21,429