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Matches 1 - 50 out of 8,936

Document Document Title
WO/2018/103910A1
The invention relates to a system for operating an internal combustion engine, which discharges residual heat during operation via an exhaust gas, said residual heat in turn being used in a thermodynamic cycle, in order to vaporize a wor...  
WO/2018/101303A1
This gas turbine high-temperature component is provided with: a body; a porous part through which a cooling gas can pass and which is provided as at least a part of the body or on at least a part of the body; and at least one filter that...  
WO/2018/100278A1
The invention relates to a guide vane (24) for an aircraft bypass turbomachine, the aerodynamic part (34) thereof comprising a first internal lubricant cooling passage (50a) in which heat transfer means are arranged and a second internal...  
WO/2018/099591A1
The invention relates to an exhaust gas guide section for an exhaust gas turbocharger, wherein the exhaust gas guide section (1) is designed for through flow, and wherein a wheel chamber (8) is designed for the rotatable holding of a bla...  
WO/2018/101190A1
A high-temperature component (10) for a gas turbine is provided with a main body part (40) and a porous part (42) through which a cooling gas can pass, and is configured such that, in accordance with one or both distributions of a heat l...  
WO/2018/099619A1
The invention relates to a turbocharger having a turbine, a compressor, and a bearing housing (2), wherein the turbine has a turbine housing (1), a nozzle ring (3), and a turbine rotor. The turbocharger furthermore comprises a fastening ...  
WO/2018/102644A1
A component including a wall (20) with a first surface, a second surface opposite the first surface, and at least one aperture (32) formed within the wall (20) and extending from the first surface to the second surface. At least one boss...  
WO/2018/091871A1
A turbine for a turbo-machine is proposed in which, at a gas inlet, vanes, extending from a nozzle ring though slots in a shroud, are shaped on one side to as to substantially conform to the profile of the surface of the slot, whereby a ...  
WO/2018/093627A2
An assembly comprises a cooling chamber disposed inside an airfoil of a turbine assembly. The cooling chamber is configured to direct cooling air inside of the airfoil. The assembly includes an impingement hole disposed inside the airfoi...  
WO/2018/089023A1
An end or intermediate casing for a combustion turbine engines includes prefabricated vanes of a first metal. Ends of the prefabricated vanes are then embedded within cast-in place inner and outer, annular-shaped ring castings, formed fr...  
WO/2018/089014A1
A seal assembly (10) arranged to seal a gap between a transition duct (12) of a gas turbine engine and a first stage turbine vane structure (14) is provided. A flexible seal element (26), such as cloth seal, extends between opposed sides...  
WO/2018/087701A1
The present invention relates to a method for the construction of rotor and stator elements for turbomachinery comprising: preparing a solid (14) of material to be machined; performing cuts (15', 15", 15'", 15"", 22', 22", 22'", 22"") in...  
WO/2018/084154A1
This variable nozzle unit is provided with a variable nozzle blade disposed between a hub wall surface and a shroud wall surface and capable of pivoting within a gas inflow passage about a pivot axis parallel to the rotation axis of the ...  
WO/2018/084902A1
A turbofan engine includes a core (30); and a low-pressure turbine (22) configured to drive a fan (46) to produce a fan flow that exits the engine without passing through a turbine. The fan includes a rotor having at least one rotor stag...  
WO/2018/080474A1
A liner (10) for a gas turbine engine is inserted into a channel (12) located in a inlet ring (11) of a transition duct (8). The liner is formed as a flat unitary piece with angled ends (14). The angled ends complement each other. When i...  
WO/2018/075573A1
Variable geometry turbine turbochargers with rotating guide vane members and spacer members. The spacer members are positioned in the space on the guide ring members between the ring of guide vane members and the turbine wheel.  
WO/2018/073608A1
A method is proposed for designing a turbine of a turbocharger of an engine system having an exhaust gas recirculation (EGR) path. At at least one engine speed, such as the peak torque speed, a pressure drop along the EGR path is determi...  
WO/2018/066330A1
To minimize peeling of a thermal barrier coating film in an environment containing sulfates. This thermal barrier coating film (40) has: a bond coating layer (50), which is a metal binding layer formed on a base material (110); a top coa...  
WO/2018/065307A1
The invention concerns a turbine exhaust structure (30) comprising: - a casing (34) divided into a first element (35) and a second element (36), the second element (36) being connected to the first element (35), - at least one connecting...  
WO/2018/060595A1
The invention relates to a lubricated enclosure (A) for an aircraft turbine engine, comprising a drained roller bearing (28) provided with drainage orifices (34), as well as a lubricant ejector (60) intended to limit the retention of lub...  
WO/2018/059726A1
The invention relates to a turbine (26) for an exhaust gas turbocharger (24) of an internal combustion engine (10), having a turbine housing (30) which has a receiving region (32), having a turbine wheel (34) which is arranged at least p...  
WO/2018/057086A1
A composite airfoil singlet (40) includes an airfoil (42) extending from a base (45) to a tip (46) of the airfoil, integrally formed with no more than one outer platform (50) at the tip and/or no more than one inner platform (54) at the ...  
WO/2018/054811A1
The invention relates to an assembly (1) for feeding an additional mass flow into a main mass flow, wherein the main mass flow flows along an axis of rotation, the feed and the axis of rotation being inclined in relation to one another.  
WO/2018/046423A1
The invention relates to methods for clear position determination and identification of a turbine blade (11) of a high-pressure turbine stage (10) of a gas turbine (1), particularly an aircraft engine, in the mounted state. The method fo...  
WO/2018/046178A1
The invention relates to a gas turbine (1) having a turbine (2) comprising a turbine casing (3), an outer (4) and inner casing part (5) between which a hot gas flows when the gas turbine (1) is in operation, wherein an annular duct (6) i...  
WO/2018/047523A1
Provided is a coating method, a coating film, and a turbine shroud. The present invention includes: a slurry deposition step of depositing a slurry containing a coarsely particulate ceramic and a finely particulate ceramic on a base mate...  
WO/2018/046180A1
The invention relates to a nozzle ring (40, 40') for a steam turbine (15), wherein the nozzle ring (40, 40') has a circular ring opening (50) and at least one Laval nozzle (45, 45') directed toward the circular ring opening (50), wherein...  
WO/2018/044571A1
A turbine stator vane with a closed-loop sequential impingement cooling circuit with an impingement cooling insert that includes a three-pass serpentine flow cooling circuit, where each leg of the circuit includes a cooling air supply ch...  
WO/2018/042649A1
This steam turbine assembling method comprises: an upper half assembling step for disposing an upper half partition plate (31) having an upper half partition plate division surface (31X), on the inner peripheral side of an upper half cas...  
WO/2018/042648A1
This steam turbine assembling method comprises: an upper half assembling step for disposing an upper half partition plate (31) having an upper half partition plate division surface (31X), on the inner peripheral side of an upper half cas...  
WO/2018/041555A1
Overall, the invention relates to a seal segment (10) for a turbine and to an assembly for sealing the gaps between seal segments (10) and stator vanes of a turbine. The seal segments comprise a plate-shaped wall (12), the first lateral ...  
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/2018/033408A1
An axial flow turbine comprising a casing (14), a rotor (12) having an axial rotational axis (Z) and rotatably mounted into said casing (14),at least one set of a plurality of moving blades (16) supported by said rotor; and at least one ...  
WO/2018/034729A1
A strut for a gas turbine engine includes a body defining a first side and an opposite second side. The first side is spaced from the second side along the circumferential direction of the gas turbine engine. Additionally, the body inclu...  
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/2018/026579A1
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/2018/021993A1
A gas turbine engine has a converging duct (10) that has combustion products flow at low mach speeds through a first portion (14) and a high mach speeds through a second portion (15). The converging duct (10) has two types of cooling sch...  
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/2018/010918A1
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/2018/002748A1
The present invention refers to a method for the assembly of a counter-rotating radial turbine, comprising: preparing a central case (9); pre-assembling a first turbine unit (33') and a second turbine unit (33"), each comprising: a half-...  
WO/2018/001651A1
A turbine (1) comprises: - an outer casing (12), - a plurality of nozzle blades (16), - a plurality of stator blades (18), - a nozzle valve casing (14) supporting the plurality of nozzle blades (16), the nozzle valve casing (14) being fi...  
WO/2018/005886A1
An annular duct including a modular annular heat exchanger for a gas turbine engine is provided, where the modular annular heat exchanger includes a plurality of radial modules in circumferentially adjacent arrangement. Each radial modul...  
WO/2018/004583A1
A stator vane assembly (10) for a gas turbine engine includes a first endwall segment (12) and a second endwall segment (14) arranged circumferentially spaced from each other, whereby a mate face gap (20) is defined between a first mate ...  
WO/2018/004097A1
The present invention relates to: a transition piece assembly having improved cooling efficiency for cooling a high-temperature region formed on the side surface of a transition piece; and a combustor including the same, and provides a t...  
WO/2017/221839A1
The present invention pertains to a variable nozzle vane for a variable-capacity turbocharger, wherein: the variable-capacity turbocharger is provided with a scroll flow channel formation part that forms a scroll flow channel toward the ...  
WO/2017/220646A1
Static blade (32) for an axial flow turbine comprising an aerofoil portion (44) having a leading edge (44a), a trailing edge (44b), a pressure side and a suction side and radially inner and outer reinforcement portions (46, 48) integral ...  
WO/2017/220881A1
Method for testing the integrity of a fluid flow regulating system for a turbomachine, the system comprising a fluid passage pipe (15) associated with a movable throttle; an actuator (21) comprising a movable actuating element, suitable ...  
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/2017/203126A1
The present application describes a casing (10), in particular an exhaust casing, for a turbomachine, comprising an inner hub (14) having an axis (A) of rotation and an outer annular ferrule (16) extending around the hub (14), said ferru...  
WO/2017/203151A1
The present application concerns a method for manufacturing a casing (10'), in particular an exhaust casing, for a turbomachine, comprising the steps consisting of: a) producing casing sectors (30a), each casing sector (30a) comprising a...  

Matches 1 - 50 out of 8,936