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Matches 451 - 500 out of 22,427

Document Document Title
WO/2017/113258A1
A sealing cover (20) used for a gas turbine (100). The gas turbine (100) comprises at least one turbine disk (143), and the sealing cover (20) is used to cover the turbine disk (143). A side wall (22a) of the sealing cover (20) is provid...  
WO/2017/114712A1
The invention relates to a rotor device (10A) of an aircraft engine, comprising a disc wheel and at least two rotor blades (14, 15) which are arranged on the disc wheel, which adjoin each other, and each of which comprises a blade platfo...  
WO/2017/108661A1
The invention relates to a turbine blade (10) for a thermal turbomachine, having a blade airfoil (20) around which a hot gas can be made to flow and which comprises a suction-side and a pressure-side side wall (22, 24). The blade airfoil...  
WO/2017/109408A1
The invention relates to a blade which comprises a blade body (30) made of anisotropic material and a leading edge shield (32) made of a material having better resistance to isolated impacts assembled on the blade body and including two ...  
WO/2017/112610A1
A component has an edge extending in a first direction. The component includes a filler disposed in the component. The filler has at least a first portion and a second portion. The first portion extends in a second direction from the edg...  
WO/2017/109404A1
The invention relates to the field of turbomachine blades, and more specifically to a leading edge shield (32) for a turbomachine blade (16), which comprises a lower canopy fin (34) and an upper canopy fin (36), each extending in the hei...  
WO/2017/110894A1
The present invention prevents decreases in cycle efficiency in a combined cycle plant without requiring a separate power source and improves the durability of a nozzle stationary blade. This steam turbine includes a high-pressure steam ...  
WO/2017/109407A1
The invention relates to the field of turbomachine blades, and more specifically to a leading edge shield (32) for a turbomachine blade (16), said leading edge shield (32) comprising a lower canopy fin (34) and an upper canopy fin (36). ...  
WO/2017/109406A1
The invention relates to the field of turbomachine blades, and more specifically to a leading edge shield (32) for a turbomachine blade (16), extending in the direction of its height from a lower end (40) to an upper end (41), having an ...  
WO/2017/110039A1
The present invention is a turbine rotor disc repairing method for removing a defective part generated in an outer peripheral portion of a turbine rotor disc having a blade groove in the outer peripheral portion and for reforming the bla...  
WO/2017/105259A1
A nozzle has an airfoil, and the nozzle is configured for use with a turbomachine. The airfoil has a throat distribution measured at a narrowest region in a pathway between adjacent nozzles, at which adjacent nozzles extend across the pa...  
WO/2017/105260A1
A blade has an airfoil, and the blade is configured for use with a turbomachine. The airfoil has a throat distribution measured at a narrowest region in a pathway between adjacent blades, at which adjacent blades extend across the pathwa...  
WO/2017/100911A9
The present invention relates to a conditioning method of gas turbine engine components (e.g. compressor blades and vanes) for increasing fuel efficiency. The gas turbine engine components are plasma treated in a high vacuum environment ...  
WO/2017/100911A1
The present invention relates to a conditioning method of gas turbine engine components (e.g. compressor blades and vanes) for increasing fuel efficiency. The gas turbine engine components are plasma treated in a high vacuum environment ...  
WO/2017/103650A1
New exemplary heat exchange configurations that incorporate internal or external surfaces equipped with perturbators, for changing the thermal behavior of the system, or for modulating the surface temperature distribution of the flow sur...  
WO/2017/105380A1
An airfoil (30) for a turbine (10), wherein the airfoil (30) includes leading (36) and trailing (38) edges and high (40) and low (42) pressure surfaces. The airfoil (30) includes a core support structure (34) having first (46) and second...  
WO/2017/105379A1
A turbine airfoil (10) includes a flow blocking structure (26) positioned in an airfoil interior (11), for displacing a coolant flow toward a pressure side (16) and a suction side (18) of an airfoil outer wall (14). The flow blocking str...  
WO/2017/104916A1
The present invention relates to a reaction-type steam turbine. More specifically, the present invention relates to a reaction-type steam turbine that has guide blades mounted on a turbine shaft located between disk blades and a steam in...  
WO/2017/102254A1
The invention relates to a rotor for a turbomachine, comprising a plurality of axially adjacently arranged rotor segments which are each provided with a central opening, an individual tie rod extending through the openings of the rotor s...  
WO/2017/098959A1
Provided are a seal structure, a turbomachine, and a method for producing a seal fin with which an excellent leak-preventing effect can be achieved and leak loss in a turbomachine can be reduced while suppressing an increase in productio...  
WO/2017/098960A1
Provided are a step seal, a seal structure, a turbomachine, and a method for producing a step seal with which an excellent leak-preventing effect can be achieved stably and leak loss in a turbomachine can be reduced stably. Disclosed is ...  
WO/2017/094292A1
A sliding component (10) provided with a wear-resistant coating comprises: a sliding component (12); and a wear-resistant coating (14) provided on a sliding surface (12a) of the sliding component (12) and formed of a cobalt alloy that co...  
WO/2017/093394A1
A method for manufacturing a component (1) of a rotating machine comprises the steps of forming a structural inner portion (2) by additive manufacturing from a first material; covering the structural inner portion (2) with a protective o...  
WO/2017/095438A1
An airfoil (10) for a turbine engine includes an array of features (22) positioned in an interior portion (11) of the airfoil (10). Each feature (22) extends from a pressure (14) side to a suction side (16). The array includes multiple r...  
WO/2017/093395A1
A device (1) for balancing a rotor (2) of a turbomachine comprises a base (3) coaxially fixable to the rotor (2)and to a driver; at least three balancing tools (4) arranged on the base (3), each balancing tool (4) defines a respective ba...  
WO/2017/093461A1
The present invention relates to a component (100) for a fluid flow engine, such as a gas turbine (100), comprising a first side (1), e.g. a top side and a second side (2), e.g. a bottom side, wherein the component (100) further comprise...  
WO/2017/095063A1
The present invention relates to a disc assembly and a turbine including the same. According to one aspect of the present invention, provided is a disc assembly comprising: a first disc engaging with a compressor section of a gas turbine...  
WO/2017/093606A1
A radial turbine impeller comprises a turbine wheel module (101) comprising a first surface and a second surface being mutually opposite in the axial direction of the radial turbine impeller. The radial turbine impeller comprises blade m...  
WO/2017/089082A1
Owing to the local thicker portion of a thermal barrier coating created by a second material, the thermal barrier coating system can be used longer or at higher temperatures.  
WO/2017/090502A1
A flow path forming plate (60i) is provided with a plate body (61i), a peripheral wall (65i), and a shelf (71). The plate body (61i) includes: a gas-path surface (64p) facing a gas flow path side; and an inner surface (64i) facing a side...  
WO/2017/088008A1
The present invention provides an energy conversion turbine having at least the following components: a central shaft having a rotational axis, a series of blades in mechanical connection with and disposed around the central shaft, where...  
WO/2017/089591A1
The invention relates to a wind turbine blade (18), including an aerodynamic shell (22) defining an inner space of the blade. The aerodynamic shell includes at least one composite laminated structure (30) comprising a plating layer (32) ...  
WO/2017/087959A1
A method for forming a vehicular brake rotor involving loading a shaped metal substrate with a mixture of metal alloying components and ceramic particles in a dieheating the contents of the die while applying pressure to melt at least on...  
WO/2017/087959A4
A method for forming a vehicular brake rotor involving loading a shaped metal substrate with a mixture of metal alloying components and ceramic particles in a dieheating the contents of the die while applying pressure to melt at least on...  
WO/2017/085380A1
The invention relates to a blade of a turbomachine guide vanes assembly, which blade is equipped with a cooling system comprising an insert (22) arranged inside an internal cavity (24) of the said blade, connected to an inlet (26) for bl...  
WO/2017/086822A1
The invention can be used in the manufacture of hollow blades, such as aircraft fan blades. An anti-adhesion coating is applied to regions that are not intended to be joined during diffusion bonding. Following the diffusion bonding of a ...  
WO/2017/085383A1
The invention relates to a method for manufacturing, by selective powder-bed fusion, a blade preform for a turbine engine including a blade (2) and at least one detachable holder (6) attached to the blade, the blade being manufactured in...  
WO/2017/085387A1
The invention relates to a turbine vane of a turbine engine such as a turbojet. Said vane includes a base supporting a blade (22a) that extends in a spanwise direction (EV) and ends in an apex (S). Said blade (22a) includes a pressure-si...  
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/2017/080645A8
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/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...  

Matches 451 - 500 out of 22,427