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Patent Searching and Data


Matches 601 - 650 out of 23,469

Document Document Title
WO/2018/138445A1
The invention relates to a method for removing at least one portion of a metal part (3) bonded to a part made of composite material (2) of the carbon-epoxy type, comprising a step of degrading the bonding interface between the metal part...  
WO/2018/140139A1
The present disclosure is directed to a gas turbine engine defining an axial centerline, a longitudinal direction, a radial direction, and a circumferential direction. The gas turbine engine includes one or more frames in which the frame...  
WO/2018/138155A1
The present disclosure is directed to a turbine engine (10) defining an axial direction and a radial direction. The turbine engine includes a fan or propeller assembly (14) comprising a gearbox; an engine core (20) comprising one or more...  
WO/2018/140111A1
The present disclosure is directed to a gas turbine engine defining a radial direction, a circumferential direction, an axial centerline along a longitudinal direction, and wherein the gas turbine engine defines an upstream end and a dow...  
WO/2018/138296A1
The present disclosure is directed to a shaft assembly (95) for a turbine engine (10), wherein the turbine engine includes a fan or propeller assembly (14) and an engine core (20), and further wherein the fan or propeller assembly includ...  
WO/2018/138438A1
The invention relates to a wheel blade (40) for a turbomachine compressor. The blade (40) comprises a body (41) extending between the root (P) of the blade in the direction of the height (Y-Y) of the blade. The body (41) extends from a l...  
WO/2018/138439A1
The invention relates to a vane configured to be placed with a plurality of identical vanes so as to form an impeller of an aeronautical engine, the impeller defining an axis, the vane including a blade (10) having a leading edge (10a) a...  
WO/2018/135283A1
In the present invention, a structure for cooling a turbine blade (1) is provided with: a cooling passage (17) formed between a first blade wall (3) curved in a concave shape with respect to a high-temperature gas flow passage (GP) and a...  
WO/2018/135212A1
This steam turbine (10) is provided with: a rotor (12); a casing (20) for rotatably housing the rotor (12); and a first stage (40) including a first-stage stator blade (42) fixed to an inner wall part (22) of the casing (20) and a first-...  
WO/2018/134093A1
The invention relates to a method for producing a cavity (4) in a blade platform (3) of a blade (1), in particular of a turbine blade, as part of a blade-platform cooling system, wherein the method has the steps of: producing a first bor...  
WO/2018/136182A1
The present disclosure is directed to a gas turbine engine defining a radial direction, a circumferential direction, an axial centerline along a longitudinal direction, and wherein the gas turbine engine defines an upstream end and a dow...  
WO/2018/136042A1
A turbine element for high pressure drop and heat transfer. The turbine element includes a plurality of elements (16) radially placed in columns together aligned in a series of rows of at least four rows across an interior surface of an ...  
WO/2018/136162A1
The present disclosure is directed to a gas turbine engine defining a longitudinal direction, a radial direction, and a circumferential direction, and wherein the gas turbine engine defines an upstream end and a downstream end along the ...  
WO/2018/132629A1
A method is provided for machining an airfoil section (12) of a turbine blade or vane produced by a casting process. The airfoil section (12) has an outer wall (18) delimiting an airfoil interior having one or more internal cooling passa...  
WO/2018/132123A1
The invention is related to a stator vane assembly for a gas turbine engine in which both higher pressure cooling air and lower pressure cooling air are both supplied to the stator vane assembly to cool both an airfoil (20) and inner and...  
WO/2018/130615A1
The invention relates to a process of obtainment of a dense hydrophobic icephobic wear- resistant coating by means of Cold Gas Spray technique, to the coatings obtained by said process, its use as coating in wind turbine blades, to a win...  
WO/2018/132161A2
A tip cooling apparatus for a turbine airfoil includes: a tip cap; a pair of spaced-apart tip walls connected to, extending around, and projecting outwardly from the tip cap so as to surround a central portion of the tip cap; a pocket de...  
WO/2018/131213A1
This radial-inflow-type turbine comprises: a turbine wheel including a rotor blade wherein a hub-side end of a front edge is located more toward an inner side, in the radial direction, than a shroud-side end of the front edge; and a hous...  
WO/2018/132084A1
The invention relates to a rotor (1) for a turbomachine (2) having an annular flow path (3) as seen in cross section, com-prising at least two shaft collars (5, 6) that are arranged axially adjacently and at a predetermined spacing, form...  
WO/2018/128609A1
A turbine rotating component (18) includes an airfoil (20) extending radially from a platform (40). An axial end face (44) of the platform (40) faces a seal gap (50) between the rotating component (18) and a stationary component (12). Th...  
WO/2018/127664A1
The invention relates to a part (1) comprising a substrate (3) with at least one portion made of a silicon-containing material adjacent to a substrate surface (S) and an environmental barrier (2) formed on the substrate surface and compr...  
WO/2018/129438A1
Various arrangements of a turbine for a rotating coalescer element of a crankcase ventilation system for an internal combustion engine are described. In some arrangements, the turbine is an impulse turbine, which is also known as a pelto...  
WO/2018/127652A1
The present invention relates to a part (1) comprising a substrate (3) with at least one portion made of a silicon-containing material adjacent to a substrate surface (S) and an environmental barrier (2) formed on the substrate surface a...  
WO/2018/123045A1
A scroll part of a turbine housing is configured such that a concave distribution is included in at least part of a first graph of which the horizontal axis is an angular position θ in the circumferential direction of the scroll part an...  
WO/2018/115763A1
A turbomachine (10) comprising a fan (12) shaft driven by a turbine shaft (16) by the intermediary of a rotational speed reduction device (20), said turbomachine comprising decoupling means (28) interposed between the reduction device (2...  
WO/2018/116333A1
A turbine rotor blade assembly characterized in that in the two-dimensional coordinates shown in fig. 5, A, CF, T, and L given below are set so as to satisfy 1.2 × 105 ≤ (A × CF)/(T × L) ≤ 17 × 105. Formula (1): (A × CF)/(T × L...  
WO/2018/114766A1
The invention relates to a method for joining hot gas component segments (6, 7), comprising the following steps: providing the segments (6, 7) to be joined; applying complementary joining elements (8) to the surface of the segments (6, 7...  
WO/2018/119391A1
A turbine wheel (100) for a turbocharger includes a hub (110) and blades (120). The hub includes a primary outer surface (116), a back wall surface (115), a peripheral edge (119) extending between the primary outer surface and the back w...  
WO/2018/093627A3
An assembly comprises a cooling chamber (102) disposed inside an airfoil (100) of a turbine assembly. The cooling chamber (102) is configured to direct cooling air inside of the airfoil (100). The assembly includes an impingement hole (1...  
WO/2018/114659A1
A method for producing a wind turbine rotor blade (200) is disclosed. The wind turbine rotor blade (200) has at least one inner blade section (210) and an outer blade section (220) as well as a connection element (600). The inner blade s...  
WO/2018/111407A1
The present disclosure generally relates to integrated core-shell investment casting molds that provide filament structures corresponding to cooling hole patterns in the surface of the turbine blade or stator vane, which provide a leachi...  
WO/2018/108458A1
This invention relates to a gas turbine blade (10), which has a suction side (11) and a pressure side (12) during regular use and which also has at least one internally arranged chamber (15), which is designed to conduct a cooling fluid ...  
WO/2018/110580A1
This gas turbine disassembling/assembling method is configured such that a gas turbine is provided with: a seal plate (44) that is provided to one side in an axial direction with respect to a rotor disk (18); and a seal plate movement re...  
WO/2018/108393A1
The invention relates to an anti-icing turbomachine blade (26), in particular for a low-pressure compressor or an intermediate-pressure compressor of a turbomachine. The blade (26) has a leading edge (28) formed by an ice-phobic surface ...  
WO/2018/111276A1
A gas turbine engine locates the rotating flange joint (25) in the pre-swirl section (20). The rotating flange joint (25) joins the compressor section (4) and the turbine section (6). The fluid flow typically used for the pre-swirl secti...  
WO/2018/111489A1
A method of selectively applying an overlay coating to a coated article and a selectively treated coated article are provided. The method includes the steps of providing the coated article having a treatment region that includes a bond c...  
WO/2018/110581A1
This gas turbine disassembling/assembling method is configured such that a gas turbine is provided with: a seal plate that is provided to one side in an axial direction with respect to a rotor disk; and a seal plate movement restriction ...  
WO/2018/111408A1
The present disclosure generally relates to integrated core-shell investment casting molds including a main core portion, a core tip portion, and a shell portion with at least one cavity between the core portion and the shell portion. Th...  
WO/2018/110827A1
The present invention provides a partial admission operation turbine apparatus comprising: a rotor portion rotatably coupled to a rotary shaft of a turbine and including a plurality of rotor blades; a nozzle portion fixedly coupled to th...  
WO/2018/110584A1
This gas turbine disassembling/assembling method comprises a seal plate restriction state switching step for switching between a seal plate unrestricted state where a seal plate movement restriction part does not restrict radial movement...  
WO/2018/103990A1
Intermediate bond-coat layer for improvement of adherence of a thermal barrier coating on a ceramic matrix composite substrate By application of aluminum or aluminum alloy (7') in an intermediate step a good ceramic coating (7) in an adh...  
WO/2018/104678A1
The invention proposes a method for simulating the distribution of blades on a turbomachine disc, the method comprising the steps of:⋅providing a plurality of blade configurations, each blade configuration being associated with a blade...  
WO/2018/103995A1
The invention relates to a method for producing a gas turbine component (1), which, during gas turbine operation in the mounted state as intended, comes into frictional contact with at least one friction partner, wherein the method has t...  
WO/2018/106539A1
A separation assembly comprises a housing, a jet that expels a fluid within the housing, and a turbine positioned within the housing. The fluid causes the turbine to rotate about a center rotational axis within the housing. The turbine c...  
WO/2018/103994A1
The use of magnesium oxide, reactive alumina and aluminium oxide as a base provides for a new erosion-resistant material upon sintering.  
WO/2018/103996A1
Continuous cracks can be optimally repaired using CMT technology by using a fluxed-core wire of solder material with a filling consisting of solder material and base material.  
WO/2018/101632A1
The disclosure relates to a carbon blade for a wind turbine with multiple down conductors, and more particularly, to a carbon blade for a wind turbine with multiple down conductors that includes multiple down conductors disposed thereon ...  
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/2018/100160A1
The invention relates to a gas turbine having at least one disk (5), wherein turbine blade elements (1) are connected by a connecting means (2) to the at least one disk (5), characterized in that the connecting means (2) in the interior ...  
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...  

Matches 601 - 650 out of 23,469