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Matches 601 - 650 out of 23,146

Document Document Title
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); -...  
WO/2017/220940A1
Disclosed is an annular shroud (10) for a bladed wheel (80), comprising an axially extending annular wall (10A) that has a plurality of axially extending slots (12), each of said slots (12) being designed to accommodate a leading edge (8...  
WO/2017/222920A1
Methods for repairing an airfoil having a damaged region are provided. The method can include removing the damaged portion from the airfoil to form an intermediate component. The damaged portion generally includes an original film hole h...  
WO/2017/222518A1
A blade and tip shroud assembly for a gas turbine engine. The assembly includes at least one blade with an airfoil extending span-wise along a radial direction. Each blade includes a blade tip. At least one tenon extends radially out fro...  
WO/2017/222678A1
Methods for repairing a component having a damaged region are provided. The method can include removing the damaged portion from the component to form an intermediate component, wherein the damaged portion has an original geometry; and a...  
WO/2017/220916A1
The invention relates to a one-piece bladed disk (5) of a turbomachine (1), in particular of a rotating part (2, 3) of said turbomachine (1), comprising: –a hub (10), said hub (10) comprising a rim (12), –a set of blades (20) extendi...  
WO/2017/222882A1
Methods for repairing a trailing edge of an airfoil are provided. The method can include removing a portion of the trailing edge of the airfoil to form an intermediate component, and then applying using additive manufacturing a replaceme...  
WO/2017/222650A1
A coating process for applying a bifurcated coating to an article is disclosed including applying an aluminizing slurry to a first portion of the article, applying a chromizing slurry to a second portion of the article, and simultaneousl...  
WO/2017/220058A1
The invention relates to a method for producing at least one component (14), in particular a component of a continuous-flow machine. The method comprises the following steps: a) additively manufacturing at least one first sub-region (12)...  
WO/2017/222516A1
The present disclosure is directed to systems and processes which prevent fluid droplet impact damage by surface engineering a respective component (2) to exhibit a water receding contact angle ≥ about 120 degrees upon contact with dro...  
WO/2017/216481A1
The invention relates to a process for manufacturing a turbomachine component comprising at least the following steps: - manufacturing an ingot made of ceramic material of eutectic composition by implementing the Czochralski process comp...  
WO/2017/060601A8
A process for manufacturing a composite material part comprises the following steps: - pressurized injecting of a slurry (150) containing a powder of refractory ceramic particles (1500) into a fibrous structure, - draining the liquid (15...  
WO/2017/217076A1
The ceramic matrix composite material component (10) is equipped with a first base material (12) and a second base material (14) respectively formed of a ceramic matrix composite material including a silicide, silicon carbide layers (16)...  
WO/2017/216225A1
A turbine blade (1) for a turbomachine, in particular a rotor blade for a gas turbine, having a blade platform (2), a blade airfoil (3) that projects from an upper side of the blade platform (2), and a blade root (4) that projects from a...  
WO/2017/080645A8
The present invention discloses a turbine engine with at least a high pressure and a low pressure turbine section comprising a casing and at least one turbine blade rotatably mounted within the casing wherein at least part of the inner s...  
WO/2016/133987A3
Cooling passages (99, 105) are formed in components for combustion turbine engines, such as blades (92), vanes (104, 106), ring segments (110) or castings in transitions (85), during investment casting, through use of ceramic shell inser...  
WO/2017/216480A1
The invention relates to a bladed wheel (23) of a turbomachine (10), comprising a disk (25) that extends about a longitudinal axis (26) in a central plane (PM), and a plurality of blades (30) that are distributed at regular intervals abo...  
WO/2017/213113A1
Corrosion resistance is enhanced while ensuring high enough heat shielding performance and erosion resistance. The present invention is provided with: a highly porous layer (6) that is formed on a heat-resistant substrate (100), that is ...  
WO/2017/209852A1
A method of fabricating a laminar composite article, includes steps of spreading a plurality of continuous fiber tows from a spool to form a first ply layer having a substantially consistent layer thickness, applying a binder to the spre...  
WO/2017/207924A1
The invention relates to a turbine vane (11) of a turbine engine such as a turboprop or a turbojet, said vane (11) comprising a root (12) supporting a blade, said vane (11) including at least one air-circulation duct for cooling said air...  
WO/2017/209853A1
A turbine assembly includes a rotor assembly including a shaft coupled to a plurality of rotor stages including a plurality of turbine blades. The shaft and the plurality of turbine blades define a wheelspace therein. The turbine assembl...  
WO/2017/209752A1
An attachment system (30) for securing a turbine blade (14) to a rotor disc (11) includes a root (28). In a plane perpendicular to a rotor axis (6), the root (28) is asymmetric about a radially extending longitudinal root axis (8). The r...  

Matches 601 - 650 out of 23,146