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Patent Searching and Data


Matches 1 - 50 out of 21,698

Document Document Title
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/2018/010918A1
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/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/2017/217076A1
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/2017/216480A1
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...  
WO/2017/207615A1
Expander (4) for use at a maximum internal operating temperature of less than or about 180°C, comprising a stationary shroud (25), a plurality of blades (10) or shrouded blades (10') arranged circumferentially about a rotor (30) and ext...  
WO/2017/205680A1
A propeller having a means for creating fluid flow in a non-axial direction and redirecting it in an axial direction.  
WO/2017/203917A1
Provided is a rotating body comprising: an impeller having a body 21, the impeller also having a surface 23 on which welding is to be performed, the surface 23 being provided on the rear surface 21b of the body 21, the impeller further h...  
WO/2017/205246A1
The present application provides a steam turbine. The steam turbine may include a number of rotor wheel slots (130), a number of buckets (120) positioned in the rotor wheel slots (130), and a radial support assembly positioned between ea...  
WO/2017/204941A1
The low pressure turbine includes a rotor, an outer casing, a plurality of stages of rotor blades, and a plurality of stages of stator vanes. The rotor includes a longitudinal centerline. The outer casing circumscribes the rotor. The plu...  
WO/2017/200549A1
A turbine blade tip shroud (22) includes a shroud base (20) extending in a circumferential direction of a turbine engine (64) and further extending in an axial direction of the turbine engine (64) from an upstream edge (56) to a downstre...  
WO/2017/200401A1
A component and method of forming a component are disclosed. The component includes a cast alloy section and an additive manufacturing section secured to the cast alloy section. Both the cast alloy section and the additive manufacturing ...  
WO/2017/200670A1
The present disclosure is directed to a shroud assembly for a gas turbine engine that includes a first shroud segment, a second shroud segment spaced from the first shroud segment, and a third shroud segment spaced from the first shroud ...  
WO/2017/200828A1
A turbine rotor shaft assembly (16) and associated turbocharger (10) that includes at least one turbine rotor member (17) having a first face (42) and an opposed second face (44); and a rotor shaft (18) having a first end (49) and an opp...  
WO/2017/200652A1
A method of damping a vibration in a rotatable member and a damping system for a rotatable machine are provided. The damping system includes one or more damping stages. The rotatable machine further comprising a casing at least partially...  
WO/2017/196498A1
An apparatus and method for flowing cooling air through an outer wall of an engine component such as an airfoil. The airfoil having the outer wall can include a skin layer and a porous layer. The skin layer can include a skin cooling cir...  
WO/2017/194860A1
A turbine ring assembly comprises a plurality of ring sectors (10) made of a ceramic matrix composite material and forming a turbine ring and a ring support structure (3) comprising a first and a second annular flange (32, 36). Each ring...  
WO/2017/195518A1
Provided is a coating structure, a turbine part having the same, and a method for manufacturing the coating structure. The coating structure is provided on a surface of a base portion including a ceramic-based composite material. The coa...  

Matches 1 - 50 out of 21,698