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Patent Searching and Data


Matches 751 - 800 out of 23,422

Document Document Title
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...  
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...  
WO/2017/195094A1
A mixed flow turbine (1) for the expansion phase of steam thermodynamic cycles of an organic Rankine cycle provided with a first section (A) in which a first expansion of a main flow of working fluid takes place, in a substantially radia...  
WO/2017/196698A1
An airfoil for a turbine engine having an engine component including an internal cooling circuit fluidly coupled to a plurality of passages within the outer wall of the engine component where cooling air moves from the internal cooling c...  
WO/2017/194886A1
The present invention relates to a composite part comprising at least: - a fibrous reinforcement comprising silicon carbide fibers having an oxygen content of less than or equal to 1% as an atomic percentage, and - a matrix present in th...  
WO/2017/196905A1
A coating system disposed on a surface of a substrate is provided. The coating system includes a bond coating on the surface of the substrate, a protective coating on the bond coating, a thermal barrier coating on the protective coating,...  
WO/2017/196298A1
A component for a combustion turbine engine has a ceramic matrix composite ("CMC") central substrate (73); with a substrate rib (77) that bridges opposed substrate sidewalls (74, 76). The central substrate (73) includes an embedded first...  
WO/2017/192247A1
A metal leading edge includes a nose positioned along the leading edge of a fan blade airfoil body. The metal leading edge also includes a first edge extending axially aftward from the nose along a pressure side of the fan blade airfoil ...  
WO/2017/191071A1
A system for cooling a blade (38) in a rotor (22) of a gas turbine (10), the blade (38) comprising: - a root (122) for connecting the blade (38) to the rotor (22), - an aerofoil (126) connected to the root (122), - a cooling passage exte...  
WO/2017/190884A1
The invention relates to a turbine housing (21) for a turbocharger (1) of an internal combustion engine, comprising - an annular duct (22) for guiding an exhaust gas mass flow (AM) to a turbine wheel (12) that can be arranged in the turb...  
WO/2017/191075A2
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/2017/190978A1
A gas turbine section with improved strut design A gas turbine section for an annular gas path is presented. The annular gas path is defined through a gas turbine engine. The gas turbine section includes an inner and an outer gas path wa...  
WO/2017/186492A1
The invention relates to a method for profiling blades of an axial turbomachine, having the steps of: a) preparing a geometric model of a blade profile (R, -1, +1); b) determining an oscillation mode of the geometric model; c) calculatin...  
WO/2017/186481A1
The invention relates to a cooling fluid distributor for distributing cooling fluid in a cavity of a turbomachine blade, having at least two partial inserts (3, 5), wherein the partial inserts (3, 5) are introduced individually into the ...  
WO/2017/189291A1
The present disclosure relates to a turbine wheel for a turbine of an exhaust gas turbocharger. The turbine wheel has a base body comprising a back wall and a plurality of turbine blades, connected to the base body, which each comprise a...  
WO/2017/189208A1
A gas turbine engine blade (10), including a base portion (12) having a cast wall, and a tip portion (14) attached to the base portion and having a wall (60) formed by an additive manufacturing process. The tip portion wall may be formed...  
WO/2017/186661A1
The present invention provides a gas turbine blade and a gas turbine, the gas turbine blade comprising: a blade profile, with a gas cooling channel provided in the blade profile; and a top sealing cover, disposed at the top of the blade ...  
WO/2017/188991A1
A staged cooling system for turbine component (10) includes a near-wall cooling channel (80) defined between an outer wall (12) of the turbine component (10) and a hollow core (30) positioned in an internal cavity (24) of the turbine com...  
WO/2017/186640A1
The invention relates in general to rotor blades and/or guide blades for a blading, that is to say the blades of a compressor or of a turbine. The invention also relates to a method for producing such a rotor blade or guide blade. The in...  
WO/2017/187050A1
A method for producing a part from composite material comprises positioning a fibrous texture (10) in a mould (110) comprising, in the lower portion of same, a part made from porous material (130) on which a first face (10b) of the textu...  
WO/2017/182423A1
The invention relates to a guide vane (1) for a fluid flow machine, in particular gas turbine, having an outer platform (2) in the properly mounted state of the guide vane, a vane leaf (6) projection from the outer platform (2), which ex...  
WO/2017/184138A1
A preloaded snubber assembly for turbine blades includes a plurality of turbine blade airfoils (10) including a trailing edge and a leading edge joined by a pressure side and a suction side to provide an outer surface (14) extending in a...  

Matches 751 - 800 out of 23,422