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WO/2015/082111A1 |
In order to prevent hot cracks caused by hot gas during welding in a zone (8) that is to be processed, residual compressive stress is created around said zone (8) by means of a welding operation.
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WO/2015/084449A2 |
A gas turbine engine component array includes first and second components each having a platform. The platforms are arranged adjacent to one another and provide a gap. A seal is arranged circumferentially between the first and second com...
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WO/2015/080797A1 |
A fan blade for a turbofan gas turbine engine is disclosed. The fan blade includes a body having a pressure side and a suction side and a cover. The suction side of the body includes an opening and at least one cavity for purposes of red...
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WO/2015/081037A1 |
According to some embodiments, a tie-bolt support assembly is provided which includes a support spring for engagement with both the tie-bolt and a rotor assembly to maintain a load path between the tie-bolt and the rotor assembly while a...
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WO/2015/081215A1 |
An airfoil blade assembly including a blade which includes a lift generating section with a first profiled body defined between a pressure surface and a suction surface. The first profiled body extends from a first leading edge to a firs...
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WO/2015/080781A2 |
Various embodiments are provided which provide an architecture for CMC plies to improve strength of damper retaining features of a turbine blade assembly. The plies may also be integrated with the platform structure to strength the CMC b...
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WO/2015/079154A1 |
The invention relates to a fan, in particular for a small turbine engine such as a jet engine, having a hub ratio corresponding to the ratio of the diameter of the inner limit of the air intake section (26) at the radially internal ends ...
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WO/2015/081041A1 |
According to exemplary embodiments, a rotor off-take assembly is provided by positioning an angled hole or aperture in a stator assembly (50). This angled hole provides improved pressure recovery and utilizes higher dynamic pressure to d...
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WO/2015/080854A1 |
A method casts a plurality of alloy parts in a mold (600; 700) having a plurality of part-forming cavities (601). The method comprises pouring a first alloy into the mold causing: the first alloy to branch into respective flows along res...
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WO/2015/078428A1 |
The invention relates to a compressor, in particular of a turbomachine. The compressor (2) comprises at least one blade ring (8; 12) and at least two ring segments (20, 22; 30, 32), wherein the blade ring (8; 12) has at least two equally...
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WO/2015/080804A1 |
A novel coating system is provided that allows for a single coating structure to exhibit properties previously considered mutually exclusive. A unique approach for tailoring specific properties of a coating structure as a function of loc...
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WO/2015/079150A1 |
The invention relates to a balanced turbine engine portion. Said portion comprises at least one angular section (21) arranged such as to form a balancing ring (20) centred on a ring axis (C). Said angular section (21) comprises a plurali...
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WO/2015/080783A2 |
A gas turbine engine airfoil includes a platform, and spaced apart walls that provide an exterior airfoil surface that extends radially from the platform to an end opposite the platform. A serpentine cooling passage is arranged between t...
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WO/2015/079403A1 |
This invention relates to a the energy converting apparatus 10 which comprises a housing 12 in the form of a sleeve and deflecting arrangements 14 which protrude from an inner surface 16 of the housing 12. The housing 12 has an inlet 18 ...
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WO/2015/079163A1 |
The invention proposes a fan, in particular for a turbomachine of small size such as a jet engine, having a hub ratio which corresponds to the ratio of the diameter of the inner limit of the incoming air stream (26) at the radially inner...
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WO/2015/077017A1 |
A gas turbine engine component includes opposing walls that provide an interior cooling passage. One of the walls has a turbulator with a hook that is enclosed within the walls.
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WO/2015/077011A1 |
A turbine engine is disclosed and includes an airflow passage including an inner surface defined by a main shroud and a shroud extension. A flow splitter is disposed radially outward of the inner surface and axially overlapping the shrou...
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WO/2015/077067A1 |
An engine component includes a gaspath wall defining a radially outward facing gaspath surface and an opposed non-gaspath surface. The gaspath surface defines a non-axisymmetric contour with a respective point of minimum radius for each ...
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WO/2015/075233A2 |
The invention relates to a guide vane assembly of a turbomachine on the basis of a modular structure, wherein the guide vane elements comprise at least an airfoil, an inner platform, an outer platform, wherein the guide vane airfoil and/...
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WO/2015/075405A1 |
The invention relates to a turbomachine (30) comprising: a compressor stage and a turbine stage, each stage comprising at least one disk (42); and a tubular shaft (31) sleeve (33) extending along the axis (32) of the turbomachine, wherei...
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WO/2015/075239A1 |
The invention relates to a blade assembly on the basis of a modular structure, wherein the blade elements comprise at least a rotor blade airfoil, a footboard mounting part (214) and a heat shield. The elements have at its one ending mea...
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WO/2015/075345A1 |
The present invention relates to an engine (1) with a modular structure comprising a plurality of coaxial modules (A, B, C) with, at one end, a first module (A) comprising a power transmission shaft (3) and a speed reduction gear (7), sa...
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WO/2015/075970A1 |
A turbine rotor assembly (1) equipped with: a rotor disk (2); multiple axial grooves (3) formed at the outer circumference of the rotor disk (2); and a rotor blade group (5n), which is arranged along the circumferential direction of the ...
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WO/2015/075347A1 |
The invention relates to a method for hybrid manufacturing of a straightener vane for an aircraft gas-turbine engine, the straightener vane including blading made of composite material, the method including placing, (E20) in an injection...
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WO/2015/076961A1 |
A gas turbine engine component comprises a casing, and a component fixed to the casing to extend from a first edge to a second edge. The component has a first side and a second side. A trench is formed within the casing adjacent the seco...
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WO/2015/076900A2 |
A fan rotor, for an aircraft engine, including at least one blade root attachment lug, each blade root attachment lug including an attachment lug surface, wherein at least one cavity is disposed on each attachment lug surface.
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WO/2015/073112A2 |
An assembly according to an exemplary aspect of the present disclosure includes, among other things, a disk, a cover plate providing a cavity at a first axial side of the disk, a passageway including an inlet provided by a notch in at le...
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WO/2015/073242A1 |
A turbine stator vane assembly for a gas turbine engine is disclosed and includes an airfoil rotatable about an axis transverse to an engine longitudinal axis. The airfoil includes outer walls defining an inner chamber between a pressure...
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WO/2015/073214A1 |
A vane array (20) adapted to be coupled to a vane carrier (10) within a gas turbine engine is provided comprising: a plurality of elongated airfoils (22) comprising at least a first airfoil and a second airfoil located adjacent to one an...
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WO/2015/073623A1 |
Yttria stabilized zirconia (YSZ) particles (40) form a thermal barrier layer (58) on a metal substrate (24). The YSZ particles have a porous interior (52, 54) and a fully melted and solidified outer shell (50). The thermal barrier layer ...
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WO/2015/073092A2 |
A gas turbine engine component includes spaced apart walls that extend in a load direction and provide a cooling passage. The cooling passage provides a tortuous passage having a generally straight portion that extends in the load direct...
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WO/2015/072256A1 |
A vane structure for an axial flow turbomachine that has: a single-vane section (1s, 2s) that has a single-vane structure formed on a portion of the length of a vane; and a tandem-vane section (1t, 2t) that is formed continuing from the ...
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WO/2015/073845A1 |
One exemplary embodiment of this disclosure relates to a method of forming an engine component. The method includes forming an engine component having an internal passageway, the internal passageway formed with an initial dimension. The ...
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WO/2015/071015A1 |
The invention relates to a coating system having two layers of porous coatings, comprising a tightly controlled and matched porosity.
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WO/2015/073202A1 |
A casting core assembly (140) includes a metallic core (144, 146, 148), a ceramic core (142) having a compartment (186) in which the portion of the metallic core is received, and a ceramic coating (260) at least partially covering the me...
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WO/2015/071141A1 |
A turbomachine component (1) including a base component (20) and a thermal barrier coating (TBC) (60) is provided. The base component (20) includes an outer wall (21) having an external surface (27) and an internal surface (29). The oute...
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WO/2015/071011A1 |
An equal and improved layer quality on surfaces with a high curvature is achieved due to geometrically adapted spraying.
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WO/2015/069673A1 |
An airfoil component includes a first segment that has a first piece of a mount and a first piece of an airfoil. The first segment is formed of a first ceramic-based material. A second segment includes a second piece of the mount and a s...
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WO/2015/067395A1 |
The invention relates to a mounting device (10) for mounting a guide blade (34) to be mounted in a blade groove (32) of a turbine (31). The mounting unit (10) comprises a clamping unit (11) and a pressing unit (12). Here, the clamping un...
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WO/2015/069464A1 |
A turbine airfoil (10) usable in a turbine engine and having at least one snubber (14) with a snubber cooling system (16) positioned therein and in communication with an airfoil cooling system (18) is disclosed. The snubber (14) may exte...
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WO/2015/069411A1 |
A gas turbine engine component includes a structure having a surface configured to be exposed to a hot working fluid. The surface includes a recessed pocket that is circumscribed by an overhang. At least one cooling groove is provided by...
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WO/2014/130134A9 |
A propeller having a central post to which one or more blades are connected. The blades are disposed and configured to pull air in from the propeller's sides toward the propeller's axis of rotation to create pressure in an area in the vi...
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WO/2015/068279A1 |
An axial flow turbine comprising solids of revolution (109, 112, 102, 118) and stationary parts (103, 101, 111), wherein the internal downstream side of a balance hole (120), which is formed in a rotor disc (112) constituting part of the...
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WO/2015/068227A1 |
The present invention provides a turbine blade, and a manufacturing method therefor, for which the durability of a thick section at a shroud contact part is improved. A plurality of turbine blades (1) are disposed lined up in the circumf...
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WO/2015/065659A1 |
A component for a gas turbine engine, according to an exemplary aspect of the present disclosure includes, among other things, an airfoil that includes a pressure side surface and a suction side surface that join together at a leading ed...
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WO/2015/064502A1 |
Provided is a nut (12) which is screwed onto an end on a first side of each of a plurality of bolts (11) that penetrate a plurality of rotary members in axial direction at a plurality of positions in a circumferential direction around an...
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WO/2015/065672A1 |
An exhaust diffuser (40) comprising an inner boundary (46) and an outer boundary (48) forming an annular gas path (50), and a plurality of strut structures (64) extending radially within the gas path. Each of the strut structures include...
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WO/2015/063021A1 |
The invention relates to a turbine blade (10) with an aerodynamic aerofoil (12), which extends from a bottom end (14) to a top end and comprises two aerofoil walls (16, 18) extending in between, which transversely thereto extend from a c...
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WO/2015/065727A1 |
A multi-wall gas turbine airfoil (192) and method of forming same using a casting core (150) having a monolithic body configured to define a pressure side wall (12), a suction side wall (14), and a third wall (16). The casting core is fo...
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WO/2015/065573A1 |
A method of forming an article includes forming a silicon-containing layer on a silicon-containing region of a surface of a substrate of the article; forming a plurality of channels and ridges in the silicon-containing layer; and forming...
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