| Document |
Document Title |
|
WO/2018/172655A1 |
A turbine ring assembly comprising ring sections (10) forming a turbine ring (1) and a ring support structure (3), each ring section (10) having, along a section plane defined by an axial direction (DA) and a radial direction (DR) of the...
|
|
WO/2018/157957A1 |
The invention relates to a turbine casing (1) for a turbine, in particular a steam turbine, having a front casing segment (3), which is formed around a turbine longitudinal axis (2) and has a first front casing part-segment (3a) and a se...
|
|
WO/2018/159686A1 |
In a rotating machine (1) a tip shroud (51A) of a moving blade (50) includes: a plurality of shroud outer peripheral surfaces (53A, 53B, 53C) provided in such a way that the radial direction positions thereof are positioned further towar...
|
|
WO/2018/154735A1 |
A steam turbine system (1) is provided with: a steam turbine (10) comprising a casing (11) into which steam is transferred from the exterior and a rotating shaft (15) provided so as to be capable of rotation around a central axis (Ac) wi...
|
|
WO/2018/155640A1 |
An axial flow rotating machine (100) comprises a rotating shaft (1), a rotor blade (4), a casing (2), and a stator blade (7). A stator blade body (70A) comprises: a stator blade first shape part (73A) in which a stator blade intermediate...
|
|
WO/2018/155652A1 |
In an axial flow rotary machine according to the present invention, a structure comprises a casing-side fin (42). An upstream-side inclined surface (45) that is inclined from the upstream side toward the downstream side is provided to a ...
|
|
WO/2018/156322A1 |
A shroud assembly for a turbine engine comprising a plurality of circumferentially arranged shroud segments having confronting end faces defining first and second radially spaced surfaces. The shroud assembly includes a forward edge span...
|
|
WO/2018/156293A1 |
A shroud assembly for a turbine engine comprising a plurality of circumferentially arranged shroud segments having confronting end faces defining first and second radially spaced surfaces. The shroud assembly includes a forward edge span...
|
|
WO/2018/156316A1 |
A shroud assembly for a turbine engine comprising a plurality of circumferentially arranged shroud segments having confronting end faces defining first and second radially spaced surfaces. The shroud assembly includes a forward edge span...
|
|
WO/2018/155635A1 |
A turbine moving blade comprises a diametrically extending blade body (50) in which a negative pressure surface (51) that faces one way in a circumferential direction and a pressure surface (52) that faces the other way in the circumfere...
|
|
WO/2018/155636A1 |
In an axial flow rotary machine according to the present invention, a moving blade (4) comprises a moving blade shroud (41) and a shroud-side fin (44), and a small gap is formed between said shroud-side fin (44) and a casing (2). The cas...
|
|
WO/2018/151251A1 |
A steam turbine is provided with: a rotating shaft (1); a moving blade (4) including a platform (43) and a moving blade main body (40); a casing (2); a stationary blade (7) including a stationary blade main body (70) and a stationary bla...
|
|
WO/2018/151259A1 |
A steam turbine plant (10) is provided with a high-pressure gland portion (23), a low-pressure gland portion (43), a gland regulator line (110) and a rotor drive steam supply line (120). The high-pressure gland portion (23) seals a gap a...
|
|
WO/2018/146946A1 |
Provided is a geothermal turbine equipped with a rotor, a casing for housing the rotor, a plurality of moving blades disposed around the rotor, a plurality of stationary blades supported on the casing, and at least one seal part provided...
|
|
WO/2018/146062A1 |
The invention relates to a guide vane (1) for a turbomachine, having a blade airfoil (2) and at least one platform (3), to which the blade airfoil (2) is connected. A cooling channel system is provided for cooling the platform (3) and th...
|
|
WO/2018/147013A1 |
Disclosed is a steam turbine which is equipped with a rotor, a casing for housing the rotor, a plurality of moving blades disposed around the rotor, and a plurality of stationary blades supported on the casing, and in which: the stationa...
|
|
WO/2018/145861A1 |
The invention relates to a sliding ring seal arrangement, comprising a sliding ring seal (2) having a rotating sliding ring (20) and a stationary sliding ring (21), which define a sealing gap (22) therebetween, and an integral safety sea...
|
|
WO/2018/144657A1 |
This application provides controlled tip balance slits (200) for turbines. An example leakage flow control system (110) for a turbine may include a flow runner (150) with a tip shroud (152), a diaphragm or a guide blade (130), an extensi...
|
|
WO/2018/132246A1 |
A blade outer air seal with a plurality of inner ring segment secured to a full annular cooled support ring, where the inner ring segments each have rows of curved teeth that form rows of curved grooves that open in a direction toward a ...
|
|
WO/2018/130766A1 |
The invention relates to a turbine ring assembly comprising a plurality of ring sections (10) consisting of a composite material with a ceramic matrix forming a turbine ring (1) and a ring-supporting structure (3), each section (10) havi...
|
|
WO/2018/131425A1 |
In order to enhance the efficiency of a gas turbine, this split ring surface-side member is included in a split ring, disposed at a position on the stationary side of the gas turbine and facing a moving blade, and forms a portion of a co...
|
|
WO/2018/128609A1 |
A turbine rotating component (18) includes an airfoil (20) extending radially from a platform (40). An axial end face (44) of the platform (40) faces a seal gap (50) between the rotating component (18) and a stationary component (12). Th...
|
|
WO/2018/128600A1 |
A gas turbine engine (10) has a side seal (25a) located between adjacent exit pieces. The side seal (25a) comprises a first seal side (23a) and a second seal side (24a) that contact each other. The first seal side (23a) has a spring (26a...
|
|
WO/2018/114756A1 |
The invention relates to a seal (1), in particular for high-temperature applications in thermal turbomachines, made of ceramic fiber composite material, wherein the seal (1) has a first section (3a) and a second section (3b), wherein the...
|
|
WO/2018/115456A1 |
The present invention relates to a method for compressing a gas mixture comprising neon, in a closed-loop cycle. The method comprises: providing a flow of the gas mixture and providing a compression device having at least one gas seal (3...
|
|
WO/2018/110581A1 |
This gas turbine disassembling/assembling method is configured such that a gas turbine is provided with: a seal plate that is provided to one side in an axial direction with respect to a rotor disk; and a seal plate movement restriction ...
|
|
WO/2018/110476A1 |
Disclosed is a gas turbine engine (1) that combusts, with a combustor (3), compressed air (CA) compressed by a compressor (2), and drives a turbine (5) by a high-temperature, high-pressure combustion gas (G) which has been generated, the...
|
|
WO/2018/109810A1 |
This turbine comprises: a balance piston provided to a turbine rotor; a plurality of balance piston seals arranged on a casing side so as to oppose the balance piston; a balance piston bleeding hole that bleeds air from between the plura...
|
|
WO/2018/110584A1 |
This gas turbine disassembling/assembling method comprises a seal plate restriction state switching step for switching between a seal plate unrestricted state where a seal plate movement restriction part does not restrict radial movement...
|
|
WO/2018/104182A1 |
The present application provides a turbine (10). The turbine (10) may include a rotor (55), a casing (200), and a gland seal system (100) positioned between the rotor (55) and the casing (25). The gland seal system (100) may include a ba...
|
|
WO/2018/099592A1 |
The invention relates to a turbocharger having an exhaust-gas-conducting section through which flow can pass, an air-conducting section through which flow can pass, and a bearing section (2) between the exhaust-gas-conducting section and...
|
|
WO/2018/099618A1 |
The invention relates to a turbocharger, comprising a turbine for expanding a first medium and a compressor for compressing a second medium by using energy obtained in the turbine as the first medium is expanded, wherein the turbine has ...
|
|
WO/2018/101190A1 |
A high-temperature component (10) for a gas turbine is provided with a main body part (40) and a porous part (42) through which a cooling gas can pass, and is configured such that, in accordance with one or both distributions of a heat l...
|
|
WO/2018/102075A2 |
An engine or engine casing having an inner annular case and an outer annular case. The engine casing is formed using an additive manufacturing technique such that the inner annular case and outer annular case is formed surrounding a holl...
|
|
WO/2018/095867A1 |
A rotary machine for acting on a fluid is proposed comprising a stationary housing (2), a rotor (3) for interacting with the fluid, a shaft (4) for rotating the rotor (3) about an axial direction (A), a bearing unit (5) for supporting th...
|
|
WO/2018/096264A1 |
The invention concerns a method for controlling a control valve (20) of a turbomachine operating at an engine speed at a cruise value (Vc) and oscillating around the cruise value (Vc) of same, the method being implemented by a calculatio...
|
|
WO/2018/091288A1 |
The invention relates to an assembly for a shroud (28) of an axial turbomachine having a rotor (12), such as a turbomachine compressor air-intake shroud (28). The assembly comprises an annular layer (32) of abradable material that is abl...
|
|
WO/2018/089014A1 |
A seal assembly (10) arranged to seal a gap between a transition duct (12) of a gas turbine engine and a first stage turbine vane structure (14) is provided. A flexible seal element (26), such as cloth seal, extends between opposed sides...
|
|
WO/2018/082907A1 |
The invention relates to a sealing segment (11) for forming a sealing ring of a rotor of a gas turbine. The T-shaped sealing segment comprises a central anchoring section (13) that extends circumferentially and radially and has an adjoin...
|
|
WO/2018/082908A1 |
The invention relates to a sealing segment (11) for forming a sealing ring of a rotor of a gas turbine and to a rotor equipped with corresponding sealing segments (11). The sealing segment (11) comprises a central anchoring section (13) ...
|
|
WO/2018/083403A1 |
The invention relates to a cooling device (11) for a turbine of a turbomachine extending along an axis, comprising at least one radially inner metal sheet (14) and a radially outer metal sheet (15) that are joined to one another and deli...
|
|
WO/2018/082837A1 |
The invention relates to a housing arrangement (10) for a turbomachine, comprising an inner housing (12), an outer housing (14) which encloses the inner housing (12) at least partially, and a sealing ring (16) for radial sealing between ...
|
|
WO/2018/085219A1 |
A flanged component (70) for a gas turbine engine (100) is disclosed herein. The flanged component (70) includes a flange body (79) with a flange mating surface (71) and a plurality of threaded features. Each threaded feature (72) includ...
|
|
WO/2018/080474A1 |
A liner (10) for a gas turbine engine is inserted into a channel (12) located in a inlet ring (11) of a transition duct (8). The liner is formed as a flat unitary piece with angled ends (14). The angled ends complement each other. When i...
|
|
WO/2018/073210A1 |
A method of machining a tip (512) profile of a blade (130, 140) for a turbomachine is provided. The method comprises coupling the blade (130, 140) to a component (110, 112, 114, 120, 124) of the turbomachine; supporting the component (11...
|
|
WO/2018/075167A1 |
A propeller assembly is provided. The propeller assembly includes a central hub including a forward end, an aft end, and a hub body extending therebetween along an axis of rotation of the central hub. The propeller assembly further inclu...
|
|
WO/2018/070282A1 |
Provided is a labyrinth seal that makes it possible to minimize leakage of a fluid. The labyrinth seal (30) is provided with: an ascending step structure stepped section (41) that is a stepped section on a high pressure side (X1); a desc...
|
|
WO/2018/071018A1 |
A bimetal thermo mechanical actuator (10) includes a multi-layer bimetal structure (22) that includes a plurality of bimetal structures (12). Each bimetal structure (12) includes a pair of metals, a structural metal (14) and a driving me...
|
|
WO/2018/065739A1 |
A movable ring assembly (4) for a turbine engine turbine (10) that is mounted between two successive rotor discs (20a) and (20b) of said turbine (10), said rotor discs (20a) and (20b) being fixed to each other by bolting, characterised i...
|
|
WO/2018/048390A1 |
A flexible seal (10) for at least one component (28) of a turbine engine includes a seal frame (12) with a first end (36) and a second end (38) joined by a first surface (32) and a second surface (34) extending in a longitudinal directio...
|
