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WO/2014/013157A9 |
The invention relates to a method for cutting a preform (1) intended for the production of a turbomachine part and comprising a weaving of a plurality of threads (9), said threads (9) comprising singles (3) that are visually identifiable...
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WO/2015/009425A1 |
A turbine engine component (100) comprises a fiber structure (125, 126) forming at least a portion of an airfoil (102). A matrix (128) embeds the fiber structure. A carbon nanotube filler (130) is in the matrix.
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WO/2015/006026A1 |
A gas turbine engine component includes a structure having a wall that provides an exterior surface. A first cooling passage is arranged adjacent to and interiorly of the wall. A second cooling passage is arranged in the wall and provide...
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WO/2015/006438A1 |
Plated polymeric gas turbine engine parts and methods for fabricating lightweight plated polymeric gas turbine engine parts are disclosed. The parts include a polymeric substrate plated with one or more metal layers. The polymeric materi...
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WO/2015/006056A1 |
A variable vane having an airfoil, an inner trunnion shaft and an outer trunnion shaft, with the outer trunnion shaft having a threaded hole and a groove extending around a circumference of the outer trunnion shaft is repaired by removin...
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WO/2015/004357A1 |
The invention relates to a device for centering a part inside a hollow shaft (10) including a tubular sleeve (26) inserted inside the shaft (10) and a plurality of wedges (46) regularly distributed around the sleeve (26) between said sle...
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WO/2015/006485A1 |
Plated polymeric gas turbine engine parts and methods for fabricating lightweight plated polymeric gas turbine engine parts are disclosed. The parts include a polymeric substrate plated with one or more metal layers. The polymeric materi...
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WO/2015/002976A1 |
A component for use in a gas turbine engine includes a first section, a second section, and a functionally graded section. The first section is made of a metal material. The second section is made of a ceramic material and/or a ceramic m...
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WO/2015/000830A2 |
The invention relates to a rotor (103) for a turbine (100), comprising a plurality of rotor components (130) lined up in the axial direction and connected by means of a connecting rod (144), wherein a groove (152) which extends in the ci...
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WO/2015/000629A1 |
The invention relates to a rotor (1) for a turbocharger device (2), having a shaft (3, 3' 3'') and having arranged and fixed axially one behind the other on the shaft (3, 3', 3'') an impeller wheel (4), a sealing bushing element (5) and ...
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WO/2014/209554A1 |
A turbine airfoil (12) usable in a turbine engine and having at least one ambient air cooling system (10) is disclosed. At least a portion of the cooling system (10) may include one or more cooling channels (16) configured to receive amb...
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WO/2014/209665A1 |
According to some embodiments, a flow surface comprises a composite material formed of a plurality of layers of said composite, and a piezoelectric actuator located within the layers or on an outer surface of the composite material. The ...
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WO/2014/209549A2 |
An apparatus (100) is presented for reducing a temperature gradient (30) of mainstream fluid (118) downstream of an airfoil (112) in a gas turbine engine (110). The apparatus includes a passage (116) in a trailing edge (114) of the airfo...
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WO/2014/209581A1 |
A method for creating a textured surface (52) of bond coat material (18) for improving the performance of a thermal barrier coating system (12). A plurality of columns (62) of bond coat material are formed by spraying (52) the material t...
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WO/2014/209558A1 |
An outer rim seal arrangement (10), including: an annular rim (70) centered about a longitudinal axis (30) of a rotor disc (31), extending fore and having a fore-end (72), an outward-facing surface (74), and an inward-facing surface (76)...
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WO/2014/209464A2 |
An airfoil component for a gas turbine engine includes a platform. The airfoil component includes a flow path surface from which an airfoil extends. A laterally extending aft surface is adjacent to the flow path surface. A contoured surf...
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WO/2014/205249A1 |
A nozzle segment for a nozzle ring of a gas turbine engine is disclosed. The nozzle segment includes a first endwall, a second endwall, and an airfoil extending between the first endwall and the second endwall. The airfoil includes a mul...
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WO/2014/204608A1 |
A vane has an airfoil extending between a radially outer platform and a radially inner platform. At least one of the platforms has nominally radially thinner portions, and a pad defining a radially thicker portion. The pad has a radial t...
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WO/2014/203907A1 |
A rotating body comprising a rotating body core (D), and a plurality of blades provided at regular intervals in a circumferential direction at the outer periphery or inner periphery of the rotating body core, the plurality of blades form...
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WO/2014/202561A1 |
Blade fastener for turbine blades The invention relates to a blade fastener (1) having a bottom surface (2) and a contact surface (3), said blade fastener (1) being substantially wedge-shaped. The blade fastener (1) is arranged under a b...
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WO/2014/204573A1 |
The present disclosure relates to composite airfoils bonded to a metallic root. A composite body (510) may be formed with a metallic co-molded detail (520). The co-molded detail (520) may be transient liquid phase (TLP) bonded to an atta...
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WO/2014/198640A1 |
The connection arrangement comprises a shaft (3) having an axial through hole (12), a tie rod (4) located inside the axial through hole (12), an impeller (2) comprising a solid hub, a plurality of blades, and an integral stub protruding ...
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WO/2014/199082A1 |
The present invention relates to a method for manufacturing a metal alloy part (PF) by spark plasma sintering, comprising the simultaneous application, inside a die (M), of a uniaxial pressure and of an electric current to a powder compo...
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WO/2014/200831A1 |
A component according to an exemplary aspect of the present disclosure includes, among other things, a shell defining an interior, a spar extending into the interior and a first flange attached to the spar. The spar is configured to pivo...
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WO/2014/200871A1 |
A turbine blade for a gas turbine engine. The turbine blade includes a base having a blade root, a platform, a cooling air inlet, and a base air passageway. The turbine blade also includes an airfoil section adjoined to the base and havi...
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WO/2014/199075A1 |
A part comprising a substrate (10), at least one portion of which adjacent to a surface of the substrate is made of a refractory material containing silicon, is protected by an environmental barrier (20) formed on the surface of the subs...
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WO/2014/200673A1 |
A turbine vane has an airfoil extending between an inner platform and an outer platform. The airfoil is hollow. A hollow within the airfoil extends between an inner leading edge to an inner trailing edge. An inner radius is defined at th...
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WO/2014/197474A1 |
A rotor disc (10) configured to reduce the likelihood of fractures developing in spindle bolts (12) in gas turbine engines (16) is disclosed. The spindle bolts (12) extend axially through the rotor disc (10) to retain the rotor assembly ...
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WO/2014/195634A1 |
The invention relates to a blade preform (46) including a strut connecting a platform (16) to a blade root portion (14) extending longitudinally in an upstream-downstream direction, an upstream web (26) and a downstream (28) web, which e...
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WO/2014/197061A2 |
A component for a gas turbine engine includes a wall that adjoins an interior cooling passage and provides an exterior surface. A film cooling hole fluidly connects the interior cooling passage and the exterior surface. The film cooling ...
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WO/2014/197119A2 |
A rotor assembly for a gas turbine engine includes a rotor defining an outer periphery; and a plurality of blades attached to the outer periphery. The plurality of blades includes a material property different than the other of the plura...
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WO/2014/197105A2 |
A rotor includes a rotor hub, a plurality of blades mounted in a circumferentially-spaced arrangement on the rotor hub and a plurality of platform segments circumferentially arranged, respectively, between neighboring ones of the blades....
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WO/2014/196987A2 |
A fan blade comprises an airfoil portion and a sheath portion. The sheath portion has a sheath head section, a first sheath flank, and a second sheath flank, both flanks extending chordwise from the forward sheath section. The sheath por...
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WO/2014/197233A1 |
A vane assembly includes a plurality of airfoils that extend from a first end to a second, opposed end. A first platform is at the first end and is joined to the plurality of airfoils. A second platform is at the second end and is joined...
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WO/2014/197043A2 |
A gas turbine engine component subjected to a flow of high temperature gas includes a wall having first and second surfaces and a cooling hole extending through the wall. The cooling hole includes an inlet located at the first surface, a...
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WO/2014/195091A1 |
A rotor assembly and a method of assembling the rotor assembly typically for a turbine engine 10 are disclosed. The rotor assembly 36 having a rotational axis 26, at least one rotor 30, a shaft 24 having an axially extending bore 44, a t...
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WO/2014/197912A1 |
A wind generator system with a plurality of lightweight, surface area adjustable airfoil/sail blades. Each blade is triangular or wedge shape with a narrow inner edge and a wide outer edge. Each blade includes an inner frame connected to...
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WO/2014/191691A1 |
A hollow vane, consisting of a main portion (1), of which the cavity (4) is closed by a cover (5), is produced by expanding the main portion (1) relative to the cover (5), for example by means of differential thermal expansion, then by p...
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WO/2014/193618A1 |
A triple hook ring segment including forward, midsection and aft mounting hooks for engagement with respective hangers formed on a ring segment carrier for supporting a ring segment panel, and defining a forward high pressure chamber and...
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WO/2014/194136A1 |
Vertical axis wind turbines are provided having foil design and geometry that facilitates lift, torque and laminar flow along a 360 degree radial. Contemplated foils are non-planar, and have a chord length that is at least three times gr...
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WO/2014/193565A1 |
Methods and materials for forming in-situ features in a CMC component (200) are described. The method of forming a ceramic matrix composite component with cooling features, comprises forming a preform tape (120), laying up (122) said pre...
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WO/2014/191670A1 |
A rotor disc blade (10) for a turbomachine made from composite material comprising a fibrous reinforcement obtained by multilayer weaving of yarns and densified by a matrix. The blade (10) comprises a portion that forms the airfoil (12) ...
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WO/2014/189702A1 |
A mixed flow turbine wheel (1) for a turbocharger includes a hub (6) extending axially between a nose (10) and a partial back wall (9) defining an axis of rotation in the axial direction. The partial back wall (9) extends circumferential...
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WO/2014/189902A1 |
A turbine blade airfoil (25, 31R, 31M, 31T, 72) comprising an outer surface shape defined by Cartesian coordinates of successive transverse profiles at radial increments as set forth in Tables 1a to 1k, wherein each table defines a trans...
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WO/2014/189564A2 |
A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a rotor having a pretrench that receives at least a portion of a tip of a stator, the portion of the tip extending radially int...
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WO/2014/188121A1 |
The invention relates to an aircraft turbopropeller (10) comprising two coaxial contra-rotating unducted propellers (12, 14'), upstream and downstream respectively, each propeller comprising an annular row of blades. The blades of the do...
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WO/2014/188961A1 |
A structure for cooling a turbine blade (1) from the inside, wherein a cooling medium passage (5) is provided inside the turbine blade (1), and this cooling medium passage (5) has a shape such that portions of multiple substantially cyli...
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WO/2014/189904A1 |
A gas turbine engine blade (10), having: an airfoil (12) having a pressure side (22) and a suction side (24); an inner platform (30), having: a gas path surface (40); a coolant surface (42); and at least one row (114) of film cooling hol...
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WO/2014/189888A1 |
A gas turbine engine blade (10) having: an airfoil (12) having a leading edge (14), a trailing edge (16), a pressure side (22), and a suction side (24); an inner platform (30) associated with a base (18) of the airfoil, wherein the inner...
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WO/2014/189875A1 |
A turbine blade tip shroud (22C, 22D) with a seal rail (32C, 32D) oriented in a circumferential direction of rotation (29) relative to a turbine axis, and extending radially outward from the tip relative to the turbine axis. A first toot...
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