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Matches 1,001 - 1,050 out of 23,782

Document Document Title
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...  
WO/2017/141712A1
Provided is a method for producing a blade structure used in a jet engine, wherein: the blade structure is provided with a plurality of blades, a support body supporting lower end sides of the blades, and a case covering upper end sides ...  
WO/2017/140979A1
Disclosed is a turbine engine comprising a rotor with a thrust washer (6) and at least one housing (24, 26, 28) in which the rotor is mounted on bearings such as to pivot about a longitudinal axis of rotation (12), a stationary thrust be...  
WO/2017/142873A1
An industrial gas turbine engine with first and stage turbine rotor blade cooling circuit in which the blade cooling air flows through a central passage within the rotor of the engine, flows through a space between first and second stage...  
WO/2017/142549A1
A process (100) for forming a component (10, 10a, 10b) is provided. The process (100) includes providing a cooling channel flow definition (25) at least partially about a core (12) comprising a ceramic matrix composite material (14). A m...  
WO/2017/142011A1
A sealing device (50) according to the present invention seals a gap between the outer peripheral surface of a rotor and the inner peripheral surface of a stator, and is provided with: a sealing ring (51) which is provided to the stator ...  
WO/2017/142657A1
A method for forming an impact weld used in an additive manufacturing process. The method includes providing a wire 12 having a powder filler metal core 14 located within a sheath 16. The wire 12 is then inserted within a conduit 18 havi...  
WO/2017/142572A1
A ceramic matrix composite ("CMC") component, such as a turbine blade (80) for a combustion turbine engine (20) that has a fiber-reinforced, solidified ceramic substrate (88). The substrate (88) has an inner layer of fibers (100), for en...  
WO/2017/137709A1
The invention relates to a ceramic core (10) used for the production of a hollow turbine blade for a turbomachine, using the lost-wax foundry technique, said blade comprising calibrated dust-removal holes extending from an apex of at lea...  
WO/2017/138795A1
The present invention relates to a power generation cycle system comprising: a pump module for allowing working fluid to flow; a first heat exchange module for receiving the working fluid from the rear end of the pump module and heating ...  
WO/2017/138982A1
A coupling assembly arranged between an input shaft and a rotor shaft of a supercharger includes a first hub, a second hub, a first side coupling assembly, a second side coupling assembly, a central hub and a plurality of coupler pins. T...  
WO/2017/137701A1
The invention relates to a system for rotating a fan (2) of a turbojet engine (1) about a first rotation axis (Ω), including a reduction gear (3) made up of a planetary gearset placed at the centre of the fan (2), which includes: a cent...  
WO/2017/133872A1
The invention relates to a method for compensating for the axial force of a rotor (2) of a gas turbine (1), having the following steps: - detecting a measurement value in order to characterize the axial thrust of the rotor (2) of the gas...  
WO/2017/136625A1
System and method for cooling an expander (100) rotor assembly. The system may include an annular body (148) disposed on a rotor disc (128) of the rotor assembly (118). The rotor disc (128) may also include a plurality of rotor blades (1...  
WO/2017/135187A1
This linear friction bonding device is for bonding, by frictional heat, a blade-side bonding surface of a blade and a disc-side bonding surface of a disc protrusion provided on the outer circumferential surface of a disc. The linear fric...  
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/2017/129455A1
A rotor disc (36) for a gas turbine (10) comprises: - at least a root cavity (75) for coupling with a blade (38, 60) of the gas turbine, - a disc cooling hole (70) for connecting the root cavity (75) with a source of a cooling gas. The d...  
WO/2017/125662A1
The invention relates to a centrifugal or mixed-flow compressor impeller comprising a hub (10) centred on an axis (XX'), a disk (11) extending radially from the hub (10), and a plurality of blades (16) carried by said disk (11), each bla...  
WO/2017/125671A1
The invention relates to a twisting torque sensor, comprising a transmission shaft (12) subjected to the torque to be measured, a reference shaft (14), and a device for measuring an angular deformation representing the torque to be measu...  
WO/2017/125344A1
A rotary machine (3) is disclosed, which comprises comprising: a rotary shaft (7) having a rotation axis (A-A), a first shaft end (7A), and a second shaft end (7B); a first bearing arrangement (10) at the first shaft end (7A); a second b...  

Matches 1,001 - 1,050 out of 23,782