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WO/2015/147672A1 |
The present invention relates to a blade (1) with an airfoil profile for a gas turbine, comprising at least two opposite walls (2) enclosing the inner part of the blade (1) comprising cooling channels (3). The airfoil profile is exten...
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WO/2015/147958A2 |
A method (200) of forming a ceramic matrix composite turbine blade (40) with squealer tip (54) and with tip flare (70) is provided. The tip flare may be located at either or both of the pressure side and the suction side. The method prov...
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WO/2015/147930A2 |
An airfoil assembly has at least one cooling hole in an aft edge of at least one platform for cooling at least one of an axially downstream airfoil root and/or tip region. The airfoil assembly may be a high pressure turbine first stage v...
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WO/2015/139945A1 |
The invention relates to a method for closing a hole (2) having a hole internal wall and an internal thread (3) with at least one internal thread lead in a component (1) made of a base material, comprising the following steps: - providin...
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WO/2015/140711A1 |
The present invention regards a radial turbomachine, comprising: a fixed case (6); at least one rotor disc (2, 2', 2") installed in the case (6) and having rotor blades (3, 3', 3") mounted on a front face (4, 4', 4") thereof; a plurality...
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WO/2015/142200A1 |
An exhaust gas diffuser (38) including: a radially-outer peripheral casing (46); a hub (42) located within said radially-outer peripheral casing and coaxial with a center axis (40) of the casing; main struts (44) located at circumferenti...
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WO/2015/139872A1 |
The invention relates to a rotor (10) for a micro-steam turbine, having a multiplicity of rotor blades (12) which are arranged on a circumferential side of the rotor (10) and which are designed to set the rotor (10) in rotation by being ...
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WO/2015/142395A2 |
The present disclosure relates generally to the field of fan blade platforms for gas turbine engines. More specifically, the present disclosure relates to a compressed chopped fiber fan blade platform for a gas turbine engine.
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WO/2015/137393A1 |
A shroud (22) is provided with shroud main bodies (22) that are secured to the blade tip of a moving blade (18) which is to be attached so as to extend from a rotor main body in the radial direction, and that are disposed so as to be mut...
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WO/2015/136276A1 |
A heat exchanger (2) comprising a duct (4) through which a first fluid (e.g. a coolant such as ram air) may flow, and one or more vanes (18) disposed within the duct (4) and configured to disrupt the flow of the first fluid through the d...
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WO/2015/138123A1 |
A method of forming a reinforced cladding (110) on a superalloy substrate (112) is described. The method includes forming a melt pool (122) including a superalloy material (116) and a plurality of discrete carbon reinforcing structures (...
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WO/2015/135787A1 |
The invention relates to a turbine blade (1) with a blade (2), a blade root (3), and a cover plate (14) between the blade root (3) and the blade (2). The cover plate (14) has a parallelogram (42) with a front surface (40) and a rear surf...
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WO/2015/133313A1 |
A seal structure (2) for sealing a gap between the outer circumferential surface (54) of a rotor (51) rotating around an axial line and the inner circumferential surface (13) of a stator (10) arranged so as to surround the rotor (51) fro...
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WO/2015/134005A1 |
A turbine airfoil (12) of a gas turbine engine with a cooling system (10), wherein the airfoil (12) has a bowed configuration is disclosed. The airfoil (12) may be configured such that the leading edge (16) or trailing edge (18), or both...
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WO/2015/134959A2 |
A turbine airfoil cooling system including a low pressure cooling system and a high pressure cooling system for a turbine airfoil of a gas turbine engine is disclosed. In at least one embodiment, the low pressure cooling system may be an...
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WO/2015/131988A1 |
The invention relates to a compressor having a compressor shaft which is arranged in a housing and on which at least one rotor is arranged. The compressor shaft with the at least one rotor is located in a compressor chamber. The rotor co...
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WO/2015/134006A1 |
A turbine airfoil (10) usable in a turbine engine (12) and having an internal cooling system (14) with a leading edge showerhead (16) having a plurality of film cooling holes (18) positioned for efficient film cooling is disclosed. The f...
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WO/2015/132091A1 |
The invention relates to a rotor component (4) for a rotor assembly of a fluid energy machine, particularly of a gas turbine, a steam turbine, a compressor or the like, wherein the rotor component (4) is at least partly made of a materia...
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WO/2015/130497A1 |
A turbomachine including a rotor having an axis and a plurality of disks positioned adjacent to each other in the axial direction, each disk including opposing axially facing surfaces and a circumferentially extending radially facing sur...
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WO/2015/130870A1 |
Turbine engine rotor (24) corresponding thru-bolts (26) and disc cavities (30) are inspected with a camera inspection system that includes one or both of a thru-bolt male threads inspection apparatus (50) and a rotor disc cavity inspecti...
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WO/2015/130381A2 |
An integrally bladed rotor includes a rotor that has a rim that provides an inner flow surface. Circumferentially spaced apart radially extending airfoils integrally with and from the rotor and joined by an airfoil fillet. An asymmetrica...
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WO/2015/128575A1 |
The invention relates to a method of manufacturing a protective edge for a blade, wherein a protective edge (30) of anodizable metal is provided, and the protective edge (30) is subjected to a micro arc oxidation electrolytic treatment. ...
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WO/2015/130382A2 |
A fan assembly for a gas turbine engine is disclosed. The fan assembly may include a rotor, a plurality of airfoils extending radially from the rotor, and a platform surrounding the rotor and including a surface that defines a flow path ...
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WO/2015/130871A1 |
Turbine engine rotor (22) corresponding thru-bolts (26) and disc cavities (24) are inspected with a camera inspection system (40,60) that includes one or both of a thru-bolt male threads inspection apparatus and a rotor disc cavity inspe...
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WO/2015/130371A2 |
A directional solidification apparatus includes a mold heating chamber, a solidification chamber, and a gas source. The solidification chamber is adjacent the mold heating chamber for solidifying molten metal formed from an air melt allo...
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WO/2015/129580A1 |
A rotor blade retention device which accurately maintains the position of a rotor blade relative to a rotor when mounting the rotor blade on the rotor, a rotor blade fixing member pressing device, and a manufacture method, assembly metho...
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WO/2015/126448A1 |
An airfoil of a turbine engine includes, pressure and suction sides extending in a radial direction from a 0% span to a 100% span position. The airfoil has a relationship between a gap/chord ratio and span position that defines a curve w...
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WO/2015/126837A1 |
An airfoil for a turbine engine includes an airfoil having pressure and suction sides extending in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip. The airfoil has a cur...
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WO/2015/126796A1 |
A compressor airfoil of a turbine engine having a geared architecture includes pressure and suction sides extending in a radial direction from a 0% span position to a 100% span position. The airfoil has a relationship between a tangentia...
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WO/2015/126449A1 |
An airfoil for a turbine engine includes an airfoil having pressure and suction sides extending in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip. The airfoil has a rel...
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WO/2015/126715A1 |
An airfoil of a turbine engine includes pressure and suction sides that extend in a radial direction from a 0% span position to a 100% span position. The airfoil has a relationship between a stagger angle and span position that defines a...
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WO/2015/126451A1 |
An airfoil for a turbine engine includes pressure and suction sides that extend in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip. The airfoil geometry corresponds to a...
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WO/2015/126774A1 |
A compressor airfoil of a turbine engine having a geared architecture includes pressure and suction sides that extend in a radial direction from a 0% span position to a 100% span position. The airfoil has a relationship between a camber ...
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WO/2015/126453A1 |
An airfoil for a turbine engine includes pressure and suction sides that extend in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip. The airfoil has a relationship betwee...
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WO/2015/126454A1 |
An airfoil for a turbine engine includes an airfoil that has pressure and suction sides that extend in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip. The airfoil has a...
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WO/2015/126452A1 |
In one exemplary embodiment, an airfoil for a turbine engine includes pressure and suction sides extending in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip. The airfoi...
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WO/2015/126450A1 |
An airfoil for a turbine engine includes pressure and suction sides extending in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip. The airfoil has a relationship between ...
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WO/2015/126798A1 |
A compressor airfoil of a turbine engine having a geared architecture includes pressure and suction sides extending in a radial direction from a 0% span position to a 100% span position. The airfoil has a relationship between a leading e...
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WO/2015/127032A1 |
An airfoil of a turbine engine includes pressure and suction sides that extend in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip. The airfoil has a relationship between...
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WO/2015/126488A2 |
A lost core mold component comprises a first leg and a second leg with a plurality of crossover members connecting the first and second legs. The plurality of crossover members includes outermost crossover members spaced from each other....
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WO/2015/126793A1 |
A compressor airfoil of a turbine engine having a geared architecture includes pressure and suction sides that extend in a radial direction from a 0% span position to a 100% span position. The airfoil has a relationship between an axial ...
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WO/2015/126941A1 |
An airfoil for a turbine engine includes pressure and suction sides that extend in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip. The airfoil has a relationship betwee...
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WO/2015/126824A1 |
An airfoil for a turbine engine includes pressure and suction sides that extend in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip. The airfoil has a relationship betwee...
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WO/2015/124760A1 |
A method of manufacturing a turbine blade (1) comprises providing a polyurethane coating (6) and a plurality of layers of composite material in a mould to form a composite turbine blade component. The coating and composite material is cu...
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WO/2015/121592A1 |
The invention relates to a clamping system (1) comprising a clamping jaw (7) mounted on the shaft of a pneumatic or hydraulic cylinder (4), wherein said cylinder has a structure which drives the clamping jaw towards its clamping position...
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WO/2015/122947A2 |
An airfoil includes an airfoil body that extends at least between leading and trailing edges, first and second sides, and radially inner and outer ends. The airfoil body includes an aluminum alloy that has a controlled crystallographic t...
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WO/2015/121000A1 |
The invention relates to a compressor blade (1) for a gas turbine (100). The compressor blade (1) has a blade substrate (2) that consists of a metal alloy and has an aluminum diffusion zone (3) on a surface of the blade substrate (2). In...
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WO/2015/121016A1 |
A method of producing a turbine rotor, in particular a steam turbine rotor, is provided. A forged and machined existing steam turbine rotor (2) having partially larger dimensions as dimensions of an intended rotor (1) is provided. The fo...
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WO/2015/120994A1 |
The invention relates to a coated high-temperature component comprising a cobalt coating that has a higher carbon content.
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WO/2015/121008A1 |
The invention relates to a component (1) for a turbomachine, the component (1) comprising a coating for minimizing thermal gradients within the component (1), the coating comprising a first coating (2) on at least a portion of a surface ...
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