Login| Sign Up| Help| Contact|

Patent Searching and Data


Matches 701 - 750 out of 23,147

Document Document Title
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/2017/100911A9
The present invention relates to a conditioning method of gas turbine engine components (e.g. compressor blades and vanes) for increasing fuel efficiency. The gas turbine engine components are plasma treated in a high vacuum environment ...  
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...  
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/2017/151110A1
A cooling system (10) configured to cool aspects of the turbine engine (12) between a compressor (14) and a turbine assembly (16) is disclosed. In at least one embodiment, the cooling system (10) may include one or more mid-frame cooling...  
WO/2017/149229A1
The invention relates to a core (16) for casting a blade of a turbomachine, said core (16) comprising a first part (17) for defining a first cavity and a second part (18) of which at least one portion (19) defines a second cavity located...  
WO/2017/148947A1
A gas turbine component (1) is described, comprising a main 5 body (80) having a front surface (77), a rear surface (78) and at least one through hole (81) extending from the front surface (77) to the rear surface (78), the through hole ...  
WO/2017/149693A1
Negative pressure surfaces (46n) of blades (42) of this radial turbine each have: a tip-side front portion (47n) including a front edge (43) and the boundary between the negative pressure surface (46n) and the tip (45); and a tip-side re...  
WO/2017/146680A1
A squealer tip (30) for a turbine blade (1) includes an end cap (32) disposed over an airfoil outer wall (12), a pressure side tip wall (34) extending radially from the end cap (32) and aligned with an outer surface (14a) of an airfoil p...  
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/2017/144160A1
The invention relates to a rotor assembly for an exhaust gas turbocharger, comprising a turbine wheel, a compressor wheel (5) connected to the turbine wheel for conjoint rotation by means of a shaft (3), and an intermediate component (8)...  
WO/2017/146726A1
There is provided a component (10, 110, 110a, 210) comprising a body (12, 112) comprising a ceramic matrix composite material (14, 114), a top surface (16, 116), a bottom surface (18, 118), and a through thickness (20, 120) between the t...  
WO/2017/146724A1
A damping system (50) and method for attaching the damping system (50) for a fabricated hollow turbine blade (10) includes an internal frame (24) that includes at least a leading edge (12), a trailing edge (14), at least one rib (22), a ...  
WO/2017/144207A1
The invention relates to a gas turbine (1) comprising a turbine section (5) with at least three turbine stages (11, 12, 13, 14), further comprising a rear hollow shaft (20) which interlocks with a turbine disk (19) of the rearmost turbin...  
WO/2017/144804A1
The invention relates to an arrangement of variable-pitch blades for an aircraft engine, said arrangement comprising a blade (21) comprising a blade root (25) for securing to a rotational support carried by a hub of the engine, and a bla...  
WO/2017/144297A1
The invention relates to a device (10) for compressing or expanding a fluid (F), comprising an impeller (14) that can be driven by a shaft (12) and a cover (16) connected, at least in sections, to the blading (14a) of the impeller (14), ...  
WO/2017/147499A1
Rotors formed by an additive manufacturing process are presented. In one example, a method of making a rotor is presented including defining a printing order for the application of a first material, and creating a plurality of lobes arra...  
WO/2017/140756A1
The invention relates to a mixed-flow turbine wheel (10) of a turbocharger, comprising a plurality of blades (14) that are distributed along the circumference of the turbine wheel (10); at least one blade (14) includes a leading edge (20...  

Matches 701 - 750 out of 23,147