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Patent Searching and Data


Matches 501 - 550 out of 22,991

Document Document Title
WO/2018/036710A1
The invention relates to a rotor blade (1) for a turbine (2), having a blade region (3), a rotor blade longitudinal axis (4) and a fir-tree root (5), arranged at the blade region (2) and extending along the rotor blade longitudinal axis ...  
WO/2018/038992A1
A gas turbine engine includes a compressor section and a turbine section together defining a core air flowpath. The rotary component is rotatable with the compressor section and the turbine section. The gas turbine engine additionally in...  
WO/2018/038457A1
Disclosed is a gas turbine blade. The gas turbine blade according to one embodiment of the present invention comprises: a turbine blade provided in a gas turbine; and a plurality of film cooling units from the leading edge to trailing ed...  
WO/2018/038994A1
The present invention is directed to repair compositions for thermal barrier coatings and methods of use thereof. The repair compositions include a ceramic composition, a colloidal solution, an aqueous binder, an aqueous dispersant, and ...  
WO/2017/196470A3
An apparatus and method for flowing cooling air through an outer wall (118) of an engine component such as an airfoil. The airfoil having the outer wall includes an opening (130). A framework (144) is disposed in the opening adapted to r...  
WO/2018/036818A1
The invention relates to a rotor of a gas turbine, comprising a first rotor disk (01) and a second rotor disk (02), between which a sealing ring formed by sealing segments (31) is arranged. For fastening, according to the invention, the ...  
WO/2018/038151A1
Provided are: a multilayer structure which has achieved a good balance between erosion resistance and fouling resistance; and a component for rotary machines, which has this multilayer structure. A multilayer structure 1 according to the...  
WO/2018/034791A1
An apparatus and method for cooling an engine component such as a turbine engine airfoil, including a wall (120) bounding an interior extending axially between a leading edge and a trailing edge and radially between a root and a tip (98)...  
WO/2018/017172A3
Airfoils for gas turbine engines are provided. In one embodiment, an airfoil formed from a ceramic matrix composite material includes opposite pressure and suction sides extending radially along a span and defining an outer surface of th...  
WO/2018/035021A1
A turbocharger (20) includes a turbine housing (22) defining a turbine housing interior (24), a turbine wheel (26) disposed within the turbine housing interior (24), a shaft (28) coupled to and rotatable by the turbine wheel (26), a comp...  
WO/2018/013422A3
A variable-cycle compressor includes: an axial-flow compressor, a flowpath downstream of the compressor, and at least one variable-cycle device operable to vary a choked flow capacity of the downstream flowpath. The compressor includes: ...  
WO/2018/034790A1
A component for a turbine engine and method for providing a cooling film on a turbine engine component, including an outer wall separating a hot fluid flow from a cooling fluid flow, using the cooling fluid flow to cool the engine compon...  
WO/2018/034778A1
An airfoil (90) for a turbine engine (10) comprises a wall bounding an interior (100) and defining a pressure sidewall and a suction sidewall, extending chord-wise from a leading edge to a trailing edge and span-wise from a root to a tip...  
WO/2018/031032A1
Airfoil outer wall thickness of a gas turbine engine blade is initially increased in a zone that is proximate the trailing edge and blade hub greater than comparable greatest wall thickness anywhere else along the trailing edge from outb...  
WO/2018/029770A1
This steam turbine blade is provided with a blade body (70) that is disposed inside a steam main flow channel formed around a rotor shaft that rotates about an axis so that main steam flows through, the blade body (70) having an airfoil ...  
WO/2018/029060A1
The invention relates to a method for joining materials, comprising: providing a first material (W1) and a second material (W2), providing the first material (W1) with a grid structure (GS) at a joining point (VS), and joining, in partic...  
WO/2018/009261A3
Ceramic matrix composite airfoils for gas turbine engines are provided. In an exemplary embodiment, an airfoil includes opposite pressure and suction sides extending radially along a span. The pressure and suction sides define an outer s...  
WO/2018/029408A1
An aspect of the invention relates to a turbo engine rotor disc that has a rotation axis and comprises, at the periphery thereof, a plurality of slots (10) regularly distributed around the rotation axis, the turbo engine rotor disc being...  
WO/2018/004767A3
An apparatus and method for cooling an engine component includes a wall (124) bounding an interior and separating a hot fluid flow from a cooling fluid flow and having a first surface along with the hot fluid flow in a hot flow path and ...  
WO/2018/026494A1
An article includes a substrate that is substantially opaque to visible light and a coating disposed on the substrate. The coating includes a coating material having an inherent index of refraction, wherein the coating has an effective i...  
WO/2018/024759A1
The invention relates to a method for producing a channel structure (200) for a turbomachine, comprising the additive production of webs (2) from a first material on a main body (1), wherein the webs (2) are constructed on the main body ...  
WO/2018/026579A1
Provided is a method including obtaining ceramic matrix composite (CMC) with a first matrix portion including a silicon carbide and silicon phase dispersed therewithin, disposing a coating thereupon to form a sealed part, and forming the...  
WO/2018/022055A1
A turbine airfoil (10) includes an elongated hollow body (26) defining a radial cavity (T1, T2) positioned in an airfoil interior (11). A pair of radial flow passes (B,E/C,D) incorporating near-wall cooling (72, 74) channels are formed o...  
WO/2018/019401A1
The invention relates to an impeller (10) for a rotor of a turbocharger, comprising blades (12) and a wheel back (16) which adjoins the blades (12) in the axial direction of the impeller (10). The wheel back (16) has a first sub-region (...  
WO/2018/022059A1
A cooling fluid feed system (10) for a turbine engine (12) for directing cooling fluids from a compressor (14) to turbine airfoils (16) is disclosed. The cooling fluid feed system (10) for a turbine engine (12) directs cooling fluids fro...  
WO/2018/020131A1
In order to compensate for the increase in a leakage rate of ventilation air originating in a circuit (1) via a labyrinth seal (15) that gradually wears at the bottom of a ventilation chamber (3), and the reduction of a purge rate via an...  
WO/2018/015985A1
The thermal insulation coated member according to an embodiment comprises a substrate, a binding layer formed on the surface of the substrate, and a thermal insulation layer formed on the surface of the binding layer. The thermal insulat...  
WO/2018/017466A1
The present disclosure generally relates to separating solid particles from an airflow in a gas turbine engine. A system for separating debris includes a first separation device (88) in fluid communication with an inlet flow path of a co...  
WO/2018/015317A1
A turbomachine component includes an aerofoil and a platform. The aerofoil has a pressure and a suction side that meet at a trailing and a leading edge. The platform includes an aerofoil side wherefrom the aerofoil extends radially, an o...  
WO/2018/011126A1
The invention relates to an improved ceramic heat shield (155) for a gas turbine (100). The ceramic heat shield (155) has a ceramic body (11) containing aluminium oxide and according to the invention has a surface layer (12) of the ceram...  
WO/2017/191075A3
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/2018/010918A1
The invention relates to a turbine vane (1) for a turbomachine, in particular for a gas turbine, comprising a vane blade (2) having a circumferential wall (5) having a pressure-side wall portion (6) and a suction-side wall portion (7) op...  
WO/2018/011081A1
The invention relates to a rotor shaft (1) for a turbine rotor of a turbine, in particular a steam turbine, having a shaft main body (2) made of a first material and at least one ring (15, 16) which is made of a second material and is at...  
WO/2018/010329A1
An apparatus for automatic angle adjustment and weighing measurement of a blade frame comprises a base frame (1). A workbench (2) and a rotary operation platform (3) are fixed to the base frame (1). A plurality of processing stations (31...  
WO/2018/009261A2
Ceramic matrix composite airfoils for gas turbine engines are provided. In an exemplary embodiment, an airfoil includes opposite pressure and suction sides extending radially along a span. The pressure and suction sides define an outer s...  
WO/2018/007274A1
The invention relates to a turbine rotor blade (1), comprising a blade root (2) and a blade airfoil (4), wherein, proceeding from an entry point (8), in particular on the blade root, at least one radial coolant channel (6) extends in a b...  
WO/2018/009419A1
An engine component (80) for a turbine engine is provided. The engine component (80) includes a substrate (82) defining a surface (84), and an energy absorbing composite (86) positioned on the surface of the substrate or within the subst...  
WO/2018/008813A1
Disclosed is a gas turbine blade. A gas turbine blade according to an embodiment of the present invention comprises: a plurality of guide ribs spaced from each other along a movement direction of a cooling fluid, which flows along a cool...  
WO/2018/009019A1
The present invention relates to a disc assembly and a turbine including the same. According to one aspect of the present invention, provided is the disc assembly comprising: a first disc engaging with a compressor section of a gas turbi...  
WO/2018/009420A1
A turbine engine that includes a stationary assembly, and a rotor assembly configured to rotate relative to the stationary assembly. The rotor assembly includes a plurality of unitary turbine (52) and fan blades (54). Each unitary turbin...  
WO/2018/007000A1
The invention relates to an impeller for a turbocharger. The impeller (1) is mounted in a housing of the turbocharger (3) in a rotatable manner about a rotational axis (4) and has an impeller hub (6) with an impeller back (7) and an empe...  
WO/2018/009264A1
A strut assembly for a gas turbine engine includes an outer structural case. The outer structural case includes a first mounting pad for mounting a first strut and a second mounting pad for mounting a second strut. The outer structural c...  
WO/2013/165518A9
A component for a gas turbine engine includes a wall and a cooling hole. The wall has a first surface and a second surface. The second surface is exposed to hot gas flow. The cooling hole extends through the wall. The cooling hole includ...  
WO/2018/007909A1
The present invention refers to a set of turbines, comprising: a first turbine (2) comprising a first shaft (7) supported in an overhung manner in a first case (8), and a first rotor (5) provided with first rotor blades (P1) and joined t...  
WO/2018/001708A1
The invention relates to a method for optimizing a design of a rotor blade (1) which has a blade root (4) and a blade airfoil (5), of a turbomachine in which an actual natural frequency of the rotor blade (1) is detected, the detected ac...  
WO/2018/005107A1
The present invention is directed to in situ methods for maintaining turbine assemblies (10). One such method includes: disposing a maintenance apparatus (20) on the rotor (12); positioning the maintenance apparatus proximate to the dama...  
WO/2018/002466A1
The invention relates to a core (18) intended for the production of a turbomachine blade by means of lost-wax moulding, said core (18) comprising a convex outer first face (20) and a concave outer second face (21), characterised in that ...  
WO/2018/000001A1
Disclosed is a method for mechanically healing functional cemented carbide or cermet surfaces (2). An exposed cemented carbide or cermet surface (2) that does not adjoin a cutting edge is blasted with a particle beam (S) in a blasting pr...  
WO/2018/002514A1
Part comprising a wall which comprises a first zone (541), a first zone (541) and the second zone (542), a network of riblets being formed on the first zone (541), the second zone (542) and also on the transition zone (54t) so as to redu...  
WO/2018/004766A1
An airfoil for a turbine engine comprises: - an outer wall defining a pressure sidewall (98) and a suction sidewall (100), extending chord-wise from a leading edge (102) to a trailing edge (104) and span-wise from a root to a tip (80); -...  

Matches 501 - 550 out of 22,991