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WO/2017/060033A1 |
Combining a precipitation-hardening nickel-base alloy with a steel or titanium substrate makes it very easy to repair parts, the nickel-base alloy having good erosion-resistant properties.
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WO/2017/060036A1 |
A device and a method by means of which the powder to be applied to another layer that is to be coated is preheated, allow the time to carry out the method to be significantly shortened.
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WO/2017/061690A1 |
A device for removing foreign material of a gas turbine is disclosed. The device for removing foreign material of a gas turbine, according to one embodiment of the present invention, comprises: a combustor casing having a first cooling a...
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WO/2017/060601A1 |
A process for manufacturing a composite material part comprises the following steps: - pressurized injecting of a slurry (150) containing a powder of refractory ceramic particles (1500) into a fibrous structure, - draining the liquid (15...
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WO/2017/055727A1 |
The invention relates to a vane (16) comprising a vane body (30) made of a composite material having a fibre-reinforced organic matrix, and a leading-edge shield (32) made of a material that has a higher resistance to periodic impacts th...
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WO/2017/057994A1 |
The disclosed invention relates to a plurality of discs having a plurality of blades arranged on the outer circumferential surfaces thereof, and to a gas turbine disc comprising: a plurality of cooling flow channels penetrating side surf...
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WO/2017/056997A1 |
This moving blade is provided with a blade body (2) in which a cooling flow passage (10) through which a cooling medium flows is formed. The blade body (2) includes: a top plate (4) forming an apex portion; and a thinning (6) which proje...
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WO/2017/056674A1 |
Provided is a low thermal expansion super-heat-resistant alloy which has low thermal expansion, high strength, good oxidation resistance and good creep rupture ductility, while being suitable for large-size components by being free from ...
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WO/2017/054996A1 |
The invention relates to a turbine blade (01) for a gas turbine, comprising a blade (03), which (03) comprises a blade wall (04) and a crown base (07) arranged at the free end of the blade (03). The blade wall (04) surrounds at least a f...
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WO/2017/057993A1 |
The disclosed invention relates to a gas turbine disc comprising: a rotor part comprising a plurality of blades and a plurality of discs having the plurality of blades arranged on the outer circumferential surfaces thereof; and a tie bol...
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WO/2017/057992A1 |
The disclosed invention relates to a gas turbine tip gap control assembly comprising: a casing configured so as to guide a flow of combustion gas; a plurality of blades combining, in the casing, with a rotating shaft of a turbine; and a ...
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WO/2017/055726A1 |
The invention relates to a blade (16) comprising a blade body (30) made of an organic matrix composite material and a leading edge shield (32) made of a material having a better resistance to random impacts than the composite material of...
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WO/2017/053505A2 |
A method and device for measuring dimensions of a feature on or near an object using a video inspection device. A reference surface is determined based on reference surface points on the surface of the object. One or more measurement cur...
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WO/2017/052247A1 |
A device for cooling a gas turbine is disclosed. The objective of the device for cooling a gas turbine, according to one embodiment of the present invention, is to perform cooling by independently supplying cooling air to a plurality of ...
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WO/2017/050931A1 |
The invention relates to a rotor unit (1) for a turbine, in particular a turbocharger, and to a method for producing said rotor unit. The rotor unit comprises a turbine rotor (2) produced from ceramic and a shaft (3) produced from metal,...
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WO/2017/053395A1 |
Certain embodiments are directed to a vertical axis unidirectional rotor for wave energy conversion, said rotor comprising a plurality of spatially distributed lift-type and/or drag-type blades and a shaft, said rotor performing unidirec...
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WO/2017/045823A1 |
The invention is related to a turbomachine component (1), particularly a gas turbine combustor component or burner component, comprising a body (2) with a first (20), a second (21) and a third section (22), the first, second and third se...
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WO/2017/048903A1 |
A wind turbine condition monitoring system includes a light source configured to produce an emitted light beam and a plurality of optical sensors configured to be positioned on a wind turbine to receive the emitted light beam from the li...
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WO/2017/045809A1 |
The invention relates to a gas turbine guide vane segment (1) and the corresponding method of manufacturing. The gas turbine guide vane segment (1) comprises a first guide vane part (2) comprising an aerofoil (21) and a first platform se...
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WO/2017/046942A1 |
[Problem] To provide a thermal barrier coating which can be used on a member in a system used under high-temperature, high-pressure conditions, such as a supercritical CO2 turbine, and is made of a highly durable ceramic. [Solution] A th...
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WO/2017/048683A1 |
A blade includes a blade body having a surface and a hole extending through the surface of the blade body. The hole defines a hole axis and a plane perpendicular to the hole axis. The hole has an elongated hole perimeter within the plane...
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WO/2017/047502A1 |
A rotor blade (50) includes a blade path (71) that extends in the blade height direction (Dwh), a platform path (81) formed in a platform (60), and a linking path (75) that connects from the outer surface (93) of an axial mounting sectio...
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WO/2017/046851A1 |
Provided is a turbine rotor blade manufacturing method wherein a turbine rotor blade is manufactured using a Ni-based alloy for forging, which has excellent workability and high design flexibility for a cooling structure. This turbine ro...
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WO/2017/046534A1 |
The invention relates to a nozzle sector (22) for a turbine engine. The nozzle sector comprises a radially outer platform (24), a radially inner platform (26), a first end blade (81), a second end blade (84) and at least one first centra...
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WO/2017/045738A1 |
The invention relates to a turbine wheel (10) for a turbine of an exhaust gas turbocharger, comprising at least one turbine blade (14) against which exhaust gas can flow; the maximum ratio of the wheel outlet diameter (A) of the turbine ...
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WO/2017/041182A1 |
A shear flow turbomachinery device includes a housing having housing walls defining a cavity, a shaft extending into the cavity though a shaft opening in the housing wall at an end of the cavity, a rotor coupled to the shaft within the c...
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WO/2017/041969A1 |
Arrangement (66, 112) for a gas turbine (10), comprising: a rotor disk portion (68) comprising an engaging section (70); a blade unit portion (72) comprising an engaging section (74), wherein the respective engaging sections (70, 74) are...
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WO/2017/042497A1 |
The invention proposes a method for producing a protective reinforcement for the leading edge (BA) or trailing edge of a blade (P), the leading edge (BA) or trailing edge being curved, the method comprising steps of flattening (102) a ho...
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WO/2017/039568A1 |
An air cooled turbine airfoil and method of cooling includes an outer wall (18) including pressure side wall and a suction side wall extend between a leading edge (12) and a trailing edge (14). A multiple pass serpentine flow cooling cir...
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WO/2017/039569A1 |
A turbine airfoil (10) includes an impingement structure (26A, 26B) comprising a hollow elongated main body (28) positioned in an interior portion (11) of an airfoil body (12). The main body (28) extends lengthwise along a radial directi...
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WO/2017/039607A1 |
The turbine component includes an endwall (46, 50) and an elongated airfoil (32) extending radially from the endwall (46, 50), the airfoil (32) having a leading edge (54), a trailing edge (56), and an intermediate portion (58) between th...
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WO/2017/039572A1 |
A turbine airfoil (10) includes a flow displacement element (26A-B, 26A'-B') positioned in an interior portion (11) of an airfoil body (12) between a pair of adjacent partition walls (24) and comprising a radially extending elongated mai...
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WO/2017/039566A1 |
An interlocking modular airfoil for a turbine. The airfoil includes at least one support column extending from a lower plate and at least one first filament having at least one first side aperture that receives the support column in a fi...
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WO/2017/039571A1 |
A turbine airfoil (10) includes a flow displacement element (26) occupying a space between a pair of adjacent partition walls (24) in an interior portion (11) of a generally hollow airfoil body (12). The flow displacement element (26) in...
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WO/2017/037804A1 |
This method for producing a turbine rotor (30) comprises: a shaping step (ST1) in which a base rotor material (30A) having a maximum outer diameter of at most 1000 mm is shaped from a low-alloy steel containing, in weight%, 0.20-0.35% of...
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WO/2017/036797A1 |
The invention relates to a turbine blade (10) comprising a platform edge surface (17) including an ultrasonic wave scattering feature (20) comprising surface irregularities adapted to alter a reflection path of an ultrasonic pulse wave.
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WO/2017/036625A1 |
Functional component of an engine or working machine, in particular a blade for a gas turbine, wherein the functional component in the engine or working machine can be installed such that, when in a defined installation position, it come...
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WO/2017/040111A1 |
A novel dual layer mask formulation is provided. In particular, the mask has a unique composition that protects the integrity of an underlying chromide coating, prevents chromium depletion from the chromide coating and prevents a subsequ...
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WO/2017/037399A1 |
The invention relates to a part (1) or an assembly of parts of a splitter stage of a turbofan, comprising a plurality of obstacles (4, 5, 6a, 6b) including at least one a blade (4) and at least one arm (5, 6a, 6b), and a platform (2) fro...
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WO/2017/037676A1 |
This disclosure describes a removable flow control device (102) which may be used in a rotating flow supply system in a gas turbine to optimize coolant flow by improving flow dynamics, reducing leakage of coolant, and reducing pressure l...
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WO/2017/033920A1 |
This turbine rotor blade (43a) is provided with a blade main body (51) and a tip shroud (52). The blade main body (51) is provided with a front edge-side cooling passage (64), a rear edge-side cooling passage (67), and an intermediate co...
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WO/2017/033726A1 |
A blade main body (51) of this gas turbine is provided with: a first cooling passage part (58); a second cooling passage part (59); a column part (60); and a plurality of protrusions. The first cooling passage part (58) is provided at th...
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WO/2017/031163A1 |
A coated substrate is provided that includes an environmental barrier coating on (e.g., directly on) a surface of a substrate (e.g., a ceramic matrix composite). The environmental barrier coating can include a barrier layer having a refr...
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WO/2017/028912A1 |
According to the invention, the use of a polymer coating (25) in the carrying flank region (24) minimizes damages. Moreover, a long-term separating effect between the components, e.g. rotor blade and rotor disk, is ensured. According to ...
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WO/2017/029008A1 |
The invention relates to steam turbine and to a method for operating said steam turbine. The steam turbine comprises a high-pressure part (1) and a separate, double-flow medium-pressure part (11), cooling steam from the high-pressure par...
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WO/2017/001752A9 |
The invention relates to a moulding unit (210) for producing a turbomachine blade blank. The moulding unit (210) has an upstream portion (270) and a downstream portion (280). According to the invention, the moulding unit (210) comprises ...
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WO/2017/026908A1 |
A deswirler (1) for a cooling system and a cooling system of a turbomachine are presented. The deswirler (1) includes a hub, a disk extending annularly around the hub, and a plurality of deswirler blades. The disk includes a hub region s...
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WO/2017/025995A1 |
A turbine blade (120), a plurality of which are arranged in a row in an annular flow path in an axial-flow turbine, is provided with: a dorsal surface (106) which curves in a convex shape; a ventral surface (107) on the opposite side to ...
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WO/2017/025451A1 |
The invention relates to a CMC component, in particular a turbine component (I), in particular a guide vane or rotor blade (L), which comprises a succession of laminate-type layers (S), the layers consisting of different ceramic fiber-co...
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WO/2017/026904A1 |
A diffuser for a turbine engine includes a first wall that extends circumferentially about a centerline axis of the turbine engine. The diffuser also includes a second wall that extends circumferentially about the centerline axis. At lea...
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