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WO/2016/142982A1 |
An axial-flow turbine (10) according to an embodiment is provided with: a plurality of heat shield plates (21) that surrounds a turbine rotor (12) via cooling spaces (S1, S2); and a leg part (40) that supports the heat shield plates (21)...
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WO/2016/142961A1 |
The purpose of the present invention is to provide a Ni-based alloy for casting that has excellent castability and high-temperature strength characteristics, and to provide a cast component for a turbine. The Ni-based alloy for casting a...
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WO/2016/143103A1 |
A turbine (10) is provided with: a turbine rotor (40) having a rotor body (41) having a cavity (42) into which cooling fluid (cf) flows, the turbine rotor (40) also having a plurality of rotor wheels (46) arranged in the axial direction ...
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WO/2016/139089A1 |
The invention relates to a method for reprocessing a component (120) locally damaged during operation, said component having an originally cubic γ/γ' microstructure, wherein the local damage resulting during operation is present in a c...
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WO/2016/139088A1 |
The invention relates to a method, in which a hollow component is produced by the method steps consisting in casting and joining a sheet metal, wherein the hollow component can comprise thin walls and has a high recession in geometry.
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WO/2016/139002A1 |
The invention relates to a rotor (1), in particular a gas turbine rotor, comprising multiple rotor discs (3), each of which has an axial through-opening, and the rotor discs are axially clamped by at least one tie rod (5) extending throu...
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WO/2016/139416A1 |
The invention concerns a fan blisk (11) for a turbomachine, said blisk (11) comprising a hub (12) delimited by an upstream face (16) and a downstream face (17) in addition to an outer peripheral face (14) and a revolving inner peripheral...
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WO/2016/134907A2 |
The invention relates to a stator or rotor blade device (1) which is cast from a metal alloy and comprises at least one blade base (3) and an airfoil (4) designed as one piece with the blade base (3), a hollow space (6) extending from th...
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WO/2016/134864A1 |
The invention relates to a wheel disk assembly (1), comprising a wheel disk (2), a plurality of blade devices (3), which are fastened along the outer circumference of the wheel disk (2), and a plurality of sealing plates (5), which are r...
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WO/2016/135779A1 |
A turbine rotor blade equipped with: an effective blade section (40); a snubber (41) provided on the outer circumferential side of the effective blade section; a platform (42) provided on the inner circumferential side of the effective b...
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WO/2016/133514A1 |
The present disclosure provides an airfoil (11) comprising an airfoil main body (12) and at least one inner wall (38). The airfoil main body (12) includes an outer wall (18) defining leading and trailing edges (20, 22), pressure and suct...
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WO/2016/133511A1 |
An airfoil (12) for a gas turbine engine in which the airfoil (12) includes an internal cooling system (10) formed in part by an interrupted internal wall (54) that distributes mechanical loads and that enables formation of inactive cavi...
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WO/2016/132044A1 |
The invention relates to a forging method using shaping equipment suitable for forging, at high temperature, a preformed metal part comprising, in the final form thereof, angular twisting undercuts (49). The method comprises: - placing t...
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WO/2016/132042A1 |
Method of manufacturing a turbomachine blade (100) made of composite material, comprising a fibrous reinforcement consolidated by a matrix, the method involving: • - creating a multilayer woven fabric so as to obtain a first fibrous pr...
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WO/2016/132502A1 |
Provided is a welding device provided with a cylindrical powder nozzle (201) for supplying powder gas, which includes a powdered welding material, toward a position of laser light irradiation on base material and a cylindrical shield noz...
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WO/2016/133982A1 |
Delamination of thermal barrier coatings ("TBC's") (276) from superalloy substrates (262) of components (260) for turbine engines (80), such as engine blades (92), vanes (104, 106), or castings in transitions (85), is inhibited during su...
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WO/2016/133987A2 |
Cooling passages (99, 105) are formed in components for combustion turbine engines, such as blades (92), vanes (104, 106), ring segments (110) or castings in transitions (85), during investment casting, through use of ceramic shell inser...
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WO/2016/133487A1 |
A turbine blade includes an airfoil having an outer wall extending radially outwardly from a platform to a blade tip. The outer wall includes a pressure sidewall and a suction sidewall, which are joined together at chordally spaced apart...
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WO/2016/133513A1 |
An airfoil (12) for a gas turbine engine in which the airfoil (12) includes an internal cooling system (10) formed in part by a segmented internal wall (54) that distributes mechanical loads is disclosed. The segmented internal wall (54)...
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WO/2016/131877A1 |
A hub (3) of a rotor (9) for a fluid flow machine is provided with helical grooves (5) for attaching replaceable blades (15) to the hub. The grooves have sidewalls with rounded portions (35) adjacent to the bottom (33). The grooves can b...
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WO/2016/133488A1 |
A turbine airfoil (10) for a gas turbine engine (12) having a more resilient film cooling hole (14) configuration is disclosed. The film cooling hole (14) may be positioned in an outer wall (16) of the airfoil (10) and may have an inlet ...
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WO/2016/129949A1 |
The present invention relates to an axial flow turbine, comprising: a rotor mounting part; a housing having a fluid supply part surrounding the rotor mounting part; a rotor which is installed at a rotation shaft installed in the housing ...
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WO/2016/129628A1 |
A flow path width at a hub-side base end (21) of a blade body (20) decreases from a front edge (25) toward a rear edge (26), exhibits a minimum value and then increases. The flow path width at a standard blade height direction position (...
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WO/2016/130300A1 |
A turbocharger wheel (4) and shaft (1) assembly exhibis a frustoconical geometry of welding zone contact surfaces extending to the outer circumference of the shaft (1). This frustoconical geometry not only allows continuous centering of ...
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WO/2016/129375A1 |
This gas turbine component comprises a metal intermediate structure (110) and a ceramic layer (130). A gas path surface (102) which faces toward a combustion gas flow path (GP) side in a radial direction (Dr), and a pair of side surfaces...
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WO/2016/127241A1 |
A two-way flow control device including: a housing defining a first opening interface and a second opening interface, a rotor having a plurality of blades, each blade controllable to be angled in a range of positive and negative blade an...
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WO/2016/129522A1 |
Provided is a production method for thermal spray particles that form a ceramic layer wherein longitudinal cracks extending in the thickness direction are dispersed in the surface direction of the ceramic layer, and a plurality of pores ...
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WO/2016/129521A1 |
A heat-shielding coating (100) is provided with: a heat-resistant alloy substrate used in a turbine member; and a ceramic layer (300) formed on the heat-resistant alloy substrate, wherein longitudinal cracks (C) extending in the thicknes...
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WO/2016/129588A1 |
Provided is a coated member which is provided with a heat shielding coating layer that exhibits excellent characteristics in a high temperature environment in which water vapor is present. A coated member (100) which is provided with a h...
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WO/2016/128664A1 |
The invention relates to a turbine engine air flow guide assembly including: a structural arm (30); and a guide vane (21) on the lower surface of the structural arm, comprising a leading edge (22), a trailing edge (23), and a camber line...
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WO/2016/126586A1 |
A process for repair of a surface (32) of a substrate (30) including the application of an energy beam (40) and vibratory mechanical energy (42) to the surface in a region of a discontinuity (34) in order to form a renewed surface (48) o...
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WO/2016/124392A1 |
The invention relates to a closing assembly (1) for closing a blade ring that is inserted into a circumferential T-groove (2) of a blade support of a turbomachine, comprising two insertion elements (3; 4), each of which has a C-shaped ba...
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WO/2016/124861A1 |
The invention relates to a blade (3) comprising at least one web (32) and a vane (30) having a leading edge (BA) and a trailing edge (BF), characterised in that it has, for at least one aerofoil of the vane (30) in the vicinity of the we...
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WO/2016/120068A1 |
The invention relates to a coupon which has a sintered shape made of two powders as a substrate, wherein the second powder has a lower melting temperature than the first powder by at least 10K, wherein a foil is provided on the sintered ...
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WO/2016/122483A1 |
A turbine airfoil (10) with a trailing edge impingement cooling system (12) configured to provide a balanced thermal profile is disclosed. The trailing edge impingement cooling system (12) may include a single trailing edge impingement c...
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WO/2016/121495A1 |
Provided is an Ni-based alloy suitable as a member for a gas turbine, the alloy having a composition comprising, in mass%, Cr: 14.0-17.0% (preferably 14.0% to less than 15.0%), Fe: 5.0-9.0%, Ti: 2.2-2.8%, Al: 0.40-1.00%, total of Nb + Ta...
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WO/2016/121193A1 |
A center vent tube aligning mechanism (13, 20, 30) which aligns a center vent tube (12) inserted through a hollow shaft (10) is provided with: an annular portion (13e, 22b, 32a) provided concentrically with the center vent tube (12), on ...
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WO/2016/122072A1 |
According to a feature, the present invention comprises: a housing having a power generator provided therein; a rotating body coupled to the housing so as to rotate; rotary support bars coupled to the outer peripheral surface of the rota...
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WO/2016/121684A1 |
A cooling system (60) is provided with a high-pressure bleed line (61) for bleeding high-pressure compressed air (A1) from a first bleed position (Pb1) of a compressor (10) and sending the air to a first high-temperature component (44a),...
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WO/2016/122478A1 |
A cooling system (10) for a turbine airfoil (12) of a turbine engine having one or more mid-chord cooling channels (16) that extend through both the airfoil (32) and a platform (18) of the airfoil (12) to provide adequate cooling the pla...
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WO/2016/119075A1 |
A power generation device using animal manure biomass, which combines press drying and direct combustion of animal manure with combustion of press liquid biogas, and comprises: a device for converting animal manure biomass energy to heat...
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WO/2016/116285A1 |
The invention relates to a securing device (2) for a turbine blade; said securing device (2) prevents the turbine blade from moving radially and axially and is characterized by a retaining piece (10) that includes a projection (15) which...
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WO/2016/118138A1 |
A gas turbine engine (10) with a seal system (12) for a turbine ring segment assembly is disclosed. The seal system (12) may include a seal plate retention device (16) that retains a seal plate (18) between adjacent ring segments positio...
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WO/2016/118135A1 |
An internal cooling system (10) for an airfoil (12) in a turbine engine (14) whereby the cooling system (10) includes a chordwise extending tip cooling channel (16) radially inward of a squealer tip (18) and formed at least in part by an...
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WO/2016/118409A1 |
An erosion strip to protect a leading edge surface is provided including an outer layer comprising a wear-resistant material. An elastomer is affixed to an interior surface of the outer layer. An adhesive layer is shaped to adhere the le...
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WO/2016/118136A1 |
A turbine airfoil (10) usable in a turbine engine and having a outer wall (16) formed from an outer wall (16) with a nonlinear outer surface (18) or a nonlinear inner surface (20), or both, for improved cooling is disclosed. In at least ...
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WO/2016/118155A1 |
A torque converter, including: an impeller including an impeller shell with an inner surface, an outer surface facing opposite the inner surface, a first radial portion substantially orthogonal to an axis of rotation for the torque conve...
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WO/2016/115352A1 |
A rotary machine (10) with at least one frangible composite blade (40) that mitigates adverse conditions associated with release of material resulting from impact damage to the composite blade (40) is provided. The composite blade (40) h...
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WO/2016/114888A1 |
A means for controlling airfoil material loss is provided. In another aspect, an airfoil material loss control structure is provided. This structure includes at least one fuse zone (102) that, during impact from a foreign object, fail be...
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WO/2016/113041A1 |
The invention relates to a method for mounting rotor blades (1) on a rotor disk (2) along a predetermined pitch circle diameter (D) in such a way that adjacent rotor blades (1), when properly mounted on the rotor disk (2) and in the cold...
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