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Matches 1 - 50 out of 20,805

Document Document Title
WO/2017/082219A1
In the present invention, an oscillating jig is provided with: an oscillating jig base that is connected to an oscillating table; a first clamp member that is provided to the oscillating jig base; a second clamp member that is provided i...  
WO/2017/082868A1
An airfoil (30) for a gas turbine (10) wherein the airfoil (30) includes an outer wall (32) having leading (34) and trailing (36) edges and convex (40) and concave (38) surfaces and wherein the outer wall (32) forms an internal cavity (5...  
WO/2017/082907A1
An airfoil (12) for a turbine engine with trailing edge cooling features including a plurality of trailing edge exit slots (30) located along an inner suction wall (26 A) of a suction side (26) of the airfoil (12) facing a pressure side ...  
WO/2017/080645A1
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/2017/078122A1
In a turbine blade, a gas turbine, an intermediate product of the turbine blade, and a method of manufacturing the turbine blade according to the present invention, a blade body (51) having hollow shape, cavities (52, 53, 54) provided in...  
WO/2017/077240A1
A method for manufacturing a component made of composite material having a body integral with at least one platform present at one end of the said body, the method comprising: - forming, from a fibrous blank, a preform of the component t...  
WO/2017/076731A1
The invention relates to a heat-insulating layer system with cooling air holes and a different heat-insulating layer in the region of the cooling air holes. By the use of two different materials in the region of the through-holes (13) an...  
WO/2017/074373A1
Composite metallic-ceramic construction blades (30) for gas turbine engine compressor or turbine sections. A ceramic splice component, such as a squealer or other blade tip (40), or leading edge (184), mechanically interlocks with a meta...  
WO/2017/074372A1
Methods for manufacture of composite construction blades (30) for gas turbine engine compressor or turbine sections. A splice component (42), such as a squealer or other blade tip (40), or leading edge (184), or repair splice mechanicall...  
WO/2017/074407A1
There are provided systems and processes (100, 100A) for attaching a non-metal component (102, 102A) comprising a ceramic matrix composite material (104), such as a transition duct (130), to a metal component (106, 106A), such as a matin...  
WO/2017/071905A1
The invention relates to a dummy wheel disk (1) for receiving blades (2) of a turbomachine during a machining process in a machining machine, comprising a disk-shaped or annular main part (3), along the circumferential surface of which s...  
WO/2017/072431A1
The invention relates to a method for producing a sealing component comprising a body (11) made of superalloy covered by a coating (13) to be placed in contact with a gas turbine blade tip (7). Steps are carried out in which: - a) the sa...  
WO/2017/074403A1
A trailing edge cooling feature for a turbine airfoil (10) includes a plurality of pins (22a-1) positioned in an airfoil interior (11) toward the trailing edge 20), each extending from the pressure side (14) to the suction side (16) and ...  
WO/2017/072469A1
The present invention relates to a method (100) for intentionally mistuning a turbine blade of a turbomachine (10), by providing raised portions (31) or slots (32), the position of which is calculated on the basis of a vibration analysis...  
WO/2017/074404A1
A turbine airfoil (10) includes an outer wall (12) delimiting an airfoil interior (11). The outer wall (12) extends span-wise in a radial direction and includes a pressure side (14) and a suction side (16) joined at a leading edge (18) a...  
WO/2017/069145A1
In the present invention the end plate (60) of a blade (50) has a gas path surface (61) facing a combustion gas flow passage (49) side, an end surface (63) along the edge of the gas path surface (61), multiple passages (81p), and a baseb...  
WO/2017/069249A1
A ventilation flow path (22), a cooling air flow path (178), a mixing space (177) and a mixed air flow path (137) are formed in this gas turbine rotor (2). The ventilation flow path (22) guides compressed air (Acom) which is axially upst...  
WO/2017/069840A1
An inset configured for use in a rotor blade is provided including a body having a shape generally complementary to a hole formed in the rotor blade. An opening extends between a first surface and a second surface of the body. The openin...  
WO/2017/069185A1
This blisk production method comprises an intermediate product formation step for forming a blisk intermediate product that has: a disk-corresponding part having a circular plate-like shape; a plurality of rotor vane-corresponding parts;...  
WO/2017/065574A1
Disclosed is a cooling apparatus for a gas turbine. A cooling apparatus for a gas turbine, according to an embodiment of the present invention, comprises: a compressor disk unit provided on the gas turbine and having a compressor disk co...  
WO/2017/063786A1
The present invention relates to a method of manufacture of a channelling tube (10). The tube is realised by rolling a metal sheet (16) in order to obtain a tube having a spiral cross section. A gap (44) is defined between two ajacent la...  
WO/2017/060044A1
The invention relates to a part and to the filling, layer by layer, of a defective spot by means of solder and parent metal. Since a defective spot is filled layer by layer (10', 11', ...), good mechanical properties are obtained for the...  
WO/2017/060086A1
The invention relates to a method for introducing a balancing mark into the compressor wheel of a turbocharger. According to the method, a milling tool is first moved in a first direction in order to introduce a recess into the compresso...  
WO/2017/059495A1
A turbine able to be used with an high-pressure and dense working fluid, the turbine comprising: a housing a shaft mounted for rotation with respect to housing; a rotor assembly attached to the shaft; at least one inlet to allow a workin...  
WO/2017/060041A1
Locally applying solder (25) to an area (7) to be repaired and welding filler therearound makes it easier to repair parts having cracks (10).  
WO/2017/060613A1
The subject of the invention is a turbine blade (12) comprising a root (P) bearing an aerofoil (11) extending in a direction of span (EV) and ending in a tip (S), this aerofoil (11) comprising a leading edge (16) and a trailing edge (17)...  
WO/2017/060603A1
The invention relates to a turbine engine part (10) comprising at least one substrate (11) and one ceramic coating (12) for protection against calcium and magnesium aluminum silicates present on the substrate, the ceramic coating includi...  
WO/2017/060033A1
Combining a precipitation-hardening nickel-base alloy with a steel or titanium substrate makes it very easy to repair parts, the nickel-base alloy having good erosion-resistant properties.  
WO/2017/060036A1
A device and a method by means of which the powder to be applied to another layer that is to be coated is preheated, allow the time to carry out the method to be significantly shortened.  
WO/2017/061690A1
A device for removing foreign material of a gas turbine is disclosed. The device for removing foreign material of a gas turbine, according to one embodiment of the present invention, comprises: a combustor casing having a first cooling a...  
WO/2017/060601A1
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/2017/055727A1
The invention relates to a vane (16) comprising a vane body (30) made of a composite material having a fibre-reinforced organic matrix, and a leading-edge shield (32) made of a material that has a higher resistance to periodic impacts th...  
WO/2017/057994A1
The disclosed invention relates to a plurality of discs having a plurality of blades arranged on the outer circumferential surfaces thereof, and to a gas turbine disc comprising: a plurality of cooling flow channels penetrating side surf...  
WO/2017/056997A1
This moving blade is provided with a blade body (2) in which a cooling flow passage (10) through which a cooling medium flows is formed. The blade body (2) includes: a top plate (4) forming an apex portion; and a thinning (6) which proje...  
WO/2017/056674A1
Provided is a low thermal expansion super-heat-resistant alloy which has low thermal expansion, high strength, good oxidation resistance and good creep rupture ductility, while being suitable for large-size components by being free from ...  
WO/2017/054996A1
The invention relates to a turbine blade (01) for a gas turbine, comprising a blade (03), which (03) comprises a blade wall (04) and a crown base (07) arranged at the free end of the blade (03). The blade wall (04) surrounds at least a f...  
WO/2017/057993A1
The disclosed invention relates to a gas turbine disc comprising: a rotor part comprising a plurality of blades and a plurality of discs having the plurality of blades arranged on the outer circumferential surfaces thereof; and a tie bol...  
WO/2017/057992A1
The disclosed invention relates to a gas turbine tip gap control assembly comprising: a casing configured so as to guide a flow of combustion gas; a plurality of blades combining, in the casing, with a rotating shaft of a turbine; and a ...  
WO/2017/055726A1
The invention relates to a blade (16) comprising a blade body (30) made of an organic matrix composite material and a leading edge shield (32) made of a material having a better resistance to random impacts than the composite material of...  
WO/2017/053505A2
A method and device for measuring dimensions of a feature on or near an object using a video inspection device. A reference surface is determined based on reference surface points on the surface of the object. One or more measurement cur...  
WO/2017/052247A1
A device for cooling a gas turbine is disclosed. The objective of the device for cooling a gas turbine, according to one embodiment of the present invention, is to perform cooling by independently supplying cooling air to a plurality of ...  
WO/2017/050931A1
The invention relates to a rotor unit (1) for a turbine, in particular a turbocharger, and to a method for producing said rotor unit. The rotor unit comprises a turbine rotor (2) produced from ceramic and a shaft (3) produced from metal,...  
WO/2017/053395A1
Certain embodiments are directed to a vertical axis unidirectional rotor for wave energy conversion, said rotor comprising a plurality of spatially distributed lift-type and/or drag-type blades and a shaft, said rotor performing unidirec...  
WO/2017/053505A3
A method and device for measuring dimensions of a feature on or near an object using a video inspection device. A reference surface is determined based on reference surface points on the surface of the object. One or more measurement cur...  
WO/2017/045823A1
The invention is related to a turbomachine component (1), particularly a gas turbine combustor component or burner component, comprising a body (2) with a first (20), a second (21) and a third section (22), the first, second and third se...  
WO/2017/048903A1
A wind turbine condition monitoring system includes a light source configured to produce an emitted light beam and a plurality of optical sensors configured to be positioned on a wind turbine to receive the emitted light beam from the li...  
WO/2017/045809A1
The invention relates to a gas turbine guide vane segment (1) and the corresponding method of manufacturing. The gas turbine guide vane segment (1) comprises a first guide vane part (2) comprising an aerofoil (21) and a first platform se...  
WO/2017/046942A1
[Problem] To provide a thermal barrier coating which can be used on a member in a system used under high-temperature, high-pressure conditions, such as a supercritical CO2 turbine, and is made of a highly durable ceramic. [Solution] A th...  
WO/2017/048683A1
A blade includes a blade body having a surface and a hole extending through the surface of the blade body. The hole defines a hole axis and a plane perpendicular to the hole axis. The hole has an elongated hole perimeter within the plane...  
WO/2017/047502A1
A rotor blade (50) includes a blade path (71) that extends in the blade height direction (Dwh), a platform path (81) formed in a platform (60), and a linking path (75) that connects from the outer surface (93) of an axial mounting sectio...  

Matches 1 - 50 out of 20,805