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WO/2017/162975A1 |
The invention relates to a platform (30) to be inserted between two adjacent blades (20) of a fan (2), and comprising a flow passage wall (34), a base wall (36), and axial and radial retaining surfaces. The flow passage wall (34) defines...
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WO/2017/164884A1 |
A gas turbine engine has an outer ring (15) formed by integrated exit pieces (10) and surrounds an inner ring (16). A seal section (20) having an L-shaped cross-section is positioned in a respective slot (11, 12) in the outer and inner r...
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WO/2017/165261A1 |
The invention relates to an oil sealing unit for a turbocharger used for sealing a passage from a bearing housing to a compressor housing having an end wall, wherein the end wall serves to delimit an oil expansion chamber in the directio...
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WO/2017/163911A1 |
This rotary machine (100) is equipped with: a rotor (1) on the outer circumferential surface (1S) of which recesses (8) are formed; stator blades (7) each having a stator blade body (70) extending from the outside toward the inside in th...
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WO/2017/159770A1 |
The present invention provides an optical measurement device, an optical measurement method, and a rotating machine with which it is possible to eliminate errors caused by thermal elongation and centrifugal elongation. The present invent...
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WO/2017/158637A1 |
A turbine equipped with a cylindrical casing and turbine stator blades arranged along the circumferential direction in the interior of the casing, said turbine blades having: a blade effective section; a cooling medium flow path for circ...
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WO/2017/159768A1 |
Provided is an optical measurement device, an optical measurement method, and a rotary machine, wherein protection is provided for optical sensors and degradation of S/N ratio is prevented. Thus, this optical measurement device equipped ...
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WO/2017/158264A1 |
The invention relates to a method for manufacturing a turbine shroud (24) for a turbomachine, involving manufacturing at least one turbine shroud segment (26), placing the turbine shroud segment (26) in a lower mold in such a way that an...
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WO/2017/158265A1 |
The invention relates to a method for manufacturing an abradable plate (32) for a turbine shroud (24, 26) of a turbomachine, said method involving preparing a mixture comprising a cobalt- or nickel-based metal powder and a powder based o...
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WO/2017/158266A1 |
The invention relates to a stator ring (20) of a flow path, preferably secondary, of a turbomachine (1), said ring (20) comprising: – an inner platform (52, 56) and an outer platform (54), – a plurality of stators (40) extending radi...
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WO/2017/153219A1 |
The invention relates to a rotor blade for a gas turbine, comprising a blade (1) extending in a radial direction, with a blade body (2) comprising a periperal wall with a pressure-side wall section (3a) and a suction-side wall section (3...
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WO/2017/154257A1 |
Tapered surface sections 21f, 22f are formed on inner-side surfaces of base sections 21a, 22a facing a flow path 14 at an outer band part 21 and an inner band part 22 of one of turbine stator blades 11, said turbine stator blades 11 bein...
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WO/2017/155497A1 |
A turbine blade (10) includes an airfoil (12) extending span-wise along a radial direction (Ra) relative to a turbine axis having a leading edge (14) and a trailing edge (16) joined by a pressures side (18) and a suction side (20), a tip...
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WO/2017/149263A1 |
A rotary seal assembly (2) comprises first and second sealing elements configured for rotational relative movement about a rotational axis and providing a sealing interface between adjacent first and second sealing faces of the first and...
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WO/2017/151146A1 |
An air cooled turbine stator vane with an impingement cooling insert (12,13) secured within a cavity, where a forward and an aft seal slot are formed between a backside surface of an airfoil and the impingement cooling insert in which fl...
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WO/2017/148891A1 |
In a gas turbine system (10) having a turbine (12) which can be impinged on by hot gas and which has a turbine wheel (18), having a combustion chamber (14) for generating hot gas for the turbine (12) and having a compressor (24) with a c...
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WO/2017/148630A1 |
The invention relates to a rotor (01) for use in a gas turbine, comprising a plurality of compressor segments (21), a plurality of central segments (31), and a plurality of turbine segments (41); the compressor segments (21) and the turb...
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WO/2017/150365A1 |
Provided are a seal structure and a turbomachine designed so as to be capable of effectively minimizing unstable vibrations. This seal structure minimizes the flow of a working fluid leak (SL) from a gap (Gd) between a rotating structure...
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WO/2017/144801A1 |
The invention relates to a device (11) for applying abradable material to a surface of an annular casing (1) of a turbomachine, the casing extending along a longitudinal axis, the device (11) comprising a support (12, 13) provided with f...
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WO/2017/145623A1 |
An insert assembly (79) equipped with an insert (80), a reinforcing member (85), and a holding member (90). The insert (80) is affixed to one end of a blade main body (51) in the radial direction. The reinforcing member (85) is arranged ...
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WO/2017/140985A1 |
The invention relates to a turbine shroud sector (10) made of ceramic matrix composite material having a portion forming an annular base (12) with an inner surface intended for defining the inner surface of a turbine ring (1) when the sh...
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WO/2017/142077A1 |
This rotary machine is provided with a stationary body having a stationary-side primary surface (13) and a rotating body having a rotation-side primary surface (54) facing the stationary-side primary surface (13). One among the stationar...
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WO/2017/141929A1 |
Provided is a brush seal with which there is little leakage of a sealed fluid. This brush seal is provided with a brush (4) having a plurality of bundled bristles, and an annular back plate (2) disposed on a low-pressure side of the brus...
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WO/2017/142011A1 |
A sealing device (50) according to the present invention seals a gap between the outer peripheral surface of a rotor and the inner peripheral surface of a stator, and is provided with: a sealing ring (51) which is provided to the stator ...
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WO/2017/142572A1 |
A ceramic matrix composite ("CMC") component, such as a turbine blade (80) for a combustion turbine engine (20) that has a fiber-reinforced, solidified ceramic substrate (88). The substrate (88) has an inner layer of fibers (100), for en...
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WO/2017/138795A1 |
The present invention relates to a power generation cycle system comprising: a pump module for allowing working fluid to flow; a first heat exchange module for receiving the working fluid from the rear end of the pump module and heating ...
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WO/2017/134976A1 |
A method for implementing an abradable coating comprising: a pattern-forming step S1 in which, using a slurry containing ceramic particles and solvent, a slurry pattern is formed on the surface of a thermal barrier coating layer; and a f...
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WO/2017/136625A1 |
System and method for cooling an expander (100) rotor assembly. The system may include an annular body (148) disposed on a rotor disc (128) of the rotor assembly (118). The rotor disc (128) may also include a plurality of rotor blades (1...
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WO/2017/125240A1 |
The invention relates to a control device for a turbocharger, comprising an exhaust gas conducting section through which fluid can flow and which includes a bypass duct for bypassing a turbine wheel that is rotatably arranged in the exha...
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WO/2017/125241A1 |
The invention relates to a control device for a turbocharger, comprising an exhaust gas conducting section through which fluid can flow and which includes a bypass duct for bypassing a turbine wheel that is rotatably arranged in the exha...
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WO/2017/125858A1 |
A method for reducing the leakage of an organic working fluid operating within a turbine (10) of an Organic Rankine Cycle system, the method comprising the injection of a fluid flow rate (Q) into a volume (I) at a static pressure lower t...
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WO/2017/123206A1 |
A flexible damper (24) for turbine blades (10) includes a plurality of segments (32) positioned together in a substantially linear pattern, each segment (32) having a first side (46), a second side (48), a top side (50), a bottom side (5...
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WO/2017/113259A1 |
A sealing telemetry assembly (20) used for a gas turbine (100) is provided. The sealing telemetry assembly (20) includes a sealing cover (22) and at least one power supply apparatus (24), wherein the sealing cover (22) is used to cover t...
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WO/2017/110224A1 |
This sealing device is provided with: fins (54) extending from a stationary body (52) toward a rotating body (51) at a gap (53) between the stationary body (52) and the rotating body (51) without being in contact with the rotating body (...
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WO/2017/103420A1 |
Disclosed are a method for manufacturing an abradable coating having variable densities and an abradable coating of said type having variable densities. According to the invention, the method involves the following steps: providing a sub...
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WO/2017/103422A1 |
Disclosed are a method for manufacturing an abradable coating having variable densities and an abradable coating of said type having variable densities. According to the invention, the method involves the following steps: providing a sub...
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WO/2017/103411A2 |
A turbine ring assembly comprises a plurality of ring sectors (10) made of a ceramic matrix composite material, forming a turbine ring (1), and a ring support structure (3) having first and second annular flanges (32, 36), each ring sect...
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WO/2017/098944A1 |
Provided are a seal fin, a seal structure, and a turbomachine in which an excellent leak-preventing effect can be achieved and leak loss in a turbomachine can be reduced. This seal fin (6) prevents fluid (SL) from leaking from a gap (Gd)...
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WO/2017/098959A1 |
Provided are a seal structure, a turbomachine, and a method for producing a seal fin with which an excellent leak-preventing effect can be achieved and leak loss in a turbomachine can be reduced while suppressing an increase in productio...
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WO/2017/098960A1 |
Provided are a step seal, a seal structure, a turbomachine, and a method for producing a step seal with which an excellent leak-preventing effect can be achieved stably and leak loss in a turbomachine can be reduced stably. Disclosed is ...
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WO/2017/098932A1 |
A seal structure 30 of a steam turbine 1 which seals leak steam flowing through a gap between a rotor 12 and a casing 10 is provided with: a plurality of sealing fins 42 which are provided projecting toward the rotor 12 from a ring main ...
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WO/2017/093648A1 |
The invention relates to a method for obtaining an annular sector of a stator (6) having a trailing edge (6A) and a leading edge (6B) and comprising a protective coating on the internal surface thereof, the method comprising: machining o...
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WO/2017/092158A1 |
Disclosed are an elastic sheet used in a servo suspended steam seal band of a turbine and a steam seal structure thereof. The elastic sheet comprises a plurality of L-shaped elastic metal sheets (1) of which the same sides are folded cor...
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WO/2017/090963A1 |
The present invention relates to a small-scale combined heat and power generator using a steam injector which employs a small-scale heat source and, more particularly, to a small-scale combined heat and power generator comprising a rotat...
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WO/2017/090709A1 |
A gas turbine (1) is provided with a compressor (10), a turbine (30), a bleed line (61), and a component introducing line (66). The bleed line (61) extracts, as bleed air, compressed air from an intermediate compression stage (19a) of th...
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WO/2017/080645A1 |
The present invention discloses a turbine engine with at least a high pressure and a low pressure turbine section comprising a casing and at least one turbine blade rotatably mounted within the casing wherein at least part of the inner s...
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WO/2017/072431A1 |
The invention relates to a method for producing a sealing component comprising a body (11) made of superalloy covered by a coating (13) to be placed in contact with a gas turbine blade tip (7). Steps are carried out in which: - a) the sa...
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WO/2017/068082A1 |
A dry gas seal (10) of a turbomachine, more particularly of a turbocompressor, for sealing a rotor-side component (11) of the turbomachine with respect to a stator-side component (12) of the turbomachine, comprising a sealing device (13)...
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WO/2017/069391A1 |
The present invention relates to a sealing assembly for a turbine, which may comprise: a first sealing member disposed at a stator of the turbine; and a second sealing member facing the first sealing member and disposed at a rotor of the...
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WO/2017/068073A1 |
Dry gas sealing system (1) for a turbomachine, in particular a turbocompressor, comprising at least one dry gas seal (4) for sealing a part (2) located on the rotor side of the turbomachine from a part (3) located on the stator side of t...
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