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Matches 51 - 100 out of 21,942

Document Document Title
WO/2018/046209A1
The invention relates to a machining device (13) for machining a rotor arranged in a turbine housing which consists of two parts, thereby forming a joint (11), in situ while the upper housing half is removed, comprising the following: - ...  
WO/2018/048486A1
A coating system for a surface of a superalloy component is provided. The coating system includes a MCrAlY coating on the surface of the superalloy component, where M is Ni, Fe, Co, or a combination thereof. The MCrAlY coating generally ...  
WO/2018/045116A1
An airfoil body may include a plurality of tubercles along a leading edge of the airfoil body and a plurality of crenulations along a trailing edge of the airfoil body, wherein at least one of a position, a size, and a shape of the plura...  
WO/2018/045033A1
A turbine rotor blade with a closed loop cooling circuit for an industrial gas turbine engine in which cooling air for the rotor blade is supplied and carried away to and from the rotor blade through the rotor shaft, and where the rotor ...  
WO/2018/041896A1
The invention relates to a method and a system for the production of blades (1) of a machine interacting with a fluid, in particular a fluid-driven machine, in particular a wind turbine, comprising a test device (19) for determining geom...  
WO/2018/040094A1
A rotary inertial impeller comprises a shaft (1) and a blade. An inner end of the blade is connected to the shaft (1). The blade is an ordinary blade or an inertial blade (7). A rotation radius R0 of the inertial blade (7) is greater tha...  
WO/2018/044270A1
A rotor stage (10) of a turbine engine includes a circumferential row of rotor segments (12), each including: first and second endwalls (14, 16) spaced apart radially, and a first and second sidewalls (18, 20) extending radially between ...  
WO/2018/044271A1
A stator stage (10) of a turbine engine includes a circumferential row of flow directing structures (12), each including: an inner endwall (14) and an outer endwall (16) spaced apart radially, and a pressure sidewall (18) and a suction s...  
WO/2018/038507A1
Disclosed is a gas turbine blade. The gas turbine blade according to one embodiment of the present invention comprises: a turbine blade (33) provided in a gas turbine; and cooling units (110), each having a cooling channel (110) for cool...  
WO/2018/036719A1
A turbomachine arrangement with a platform cooling device for a blade of a turbomachine The invention is directed to a turbomachine arrangement comprising a blade (1) of a turbomachine and a platform cooling device (10) for the blade (1)...  
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/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/2018/035021A1
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/2018/034790A1
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/2018/029408A1
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/2018/026409A3
A processing system having at least one processor operatively coupled to at least one memory. The processor receives sensor data from the at least one sensor indicating one or more characteristics of the asset. The processor generates, u...  
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/2018/026413A3
An apparatus and method for a turbine engine including an engine core having a compressor section, a combustor, and a turbine section, which are arranged to define a stator and rotor. The engine further includes a swirler to increase the...  
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/2018/022224A3
The present disclosure is directed to an engine component for a gas turbine engine, the engine component including a substrate that includes a composite fiber and defines a surface. An energy harvesting fiber is positioned within the sub...  
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/2018/017172A3
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/2018/015985A1
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/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/2018/010918A1
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/2018/009261A3
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...  

Matches 51 - 100 out of 21,942