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WO/2018/046178A1 |
The invention relates to a gas turbine (1) having a turbine (2) comprising a turbine casing (3), an outer (4) and inner casing part (5) between which a hot gas flows when the gas turbine (1) is in operation, wherein an annular duct (6) i...
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WO/2018/047523A1 |
Provided is a coating method, a coating film, and a turbine shroud. The present invention includes: a slurry deposition step of depositing a slurry containing a coarsely particulate ceramic and a finely particulate ceramic on a base mate...
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WO/2018/046180A1 |
The invention relates to a nozzle ring (40, 40') for a steam turbine (15), wherein the nozzle ring (40, 40') has a circular ring opening (50) and at least one Laval nozzle (45, 45') directed toward the circular ring opening (50), wherein...
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WO/2018/044571A1 |
A turbine stator vane with a closed-loop sequential impingement cooling circuit with an impingement cooling insert that includes a three-pass serpentine flow cooling circuit, where each leg of the circuit includes a cooling air supply ch...
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WO/2018/042649A1 |
This steam turbine assembling method comprises: an upper half assembling step for disposing an upper half partition plate (31) having an upper half partition plate division surface (31X), on the inner peripheral side of an upper half cas...
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WO/2018/042648A1 |
This steam turbine assembling method comprises: an upper half assembling step for disposing an upper half partition plate (31) having an upper half partition plate division surface (31X), on the inner peripheral side of an upper half cas...
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WO/2018/041555A1 |
Overall, the invention relates to a seal segment (10) for a turbine and to an assembly for sealing the gaps between seal segments (10) and stator vanes of a turbine. The seal segments comprise a plate-shaped wall (12), the first lateral ...
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WO/2018/044271A1 |
A stator stage (10) of a turbine engine includes a circumferential row of flow directing structures (12), each including: an inner endwall (14) and an outer endwall (16) spaced apart radially, and a pressure sidewall (18) and a suction s...
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WO/2018/033408A1 |
An axial flow turbine comprising a casing (14), a rotor (12) having an axial rotational axis (Z) and rotatably mounted into said casing (14),at least one set of a plurality of moving blades (16) supported by said rotor; and at least one ...
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WO/2018/034729A1 |
A strut for a gas turbine engine includes a body defining a first side and an opposite second side. The first side is spaced from the second side along the circumferential direction of the gas turbine engine. Additionally, the body inclu...
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WO/2018/029770A1 |
This steam turbine blade is provided with a blade body (70) that is disposed inside a steam main flow channel formed around a rotor shaft that rotates about an axis so that main steam flows through, the blade body (70) having an airfoil ...
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WO/2018/026579A1 |
Provided is a method including obtaining ceramic matrix composite (CMC) with a first matrix portion including a silicon carbide and silicon phase dispersed therewithin, disposing a coating thereupon to form a sealed part, and forming the...
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WO/2018/021993A1 |
A gas turbine engine has a converging duct (10) that has combustion products flow at low mach speeds through a first portion (14) and a high mach speeds through a second portion (15). The converging duct (10) has two types of cooling sch...
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WO/2018/015985A1 |
The thermal insulation coated member according to an embodiment comprises a substrate, a binding layer formed on the surface of the substrate, and a thermal insulation layer formed on the surface of the binding layer. The thermal insulat...
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WO/2018/010918A1 |
The invention relates to a turbine vane (1) for a turbomachine, in particular for a gas turbine, comprising a vane blade (2) having a circumferential wall (5) having a pressure-side wall portion (6) and a suction-side wall portion (7) op...
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WO/2018/002748A1 |
The present invention refers to a method for the assembly of a counter-rotating radial turbine, comprising: preparing a central case (9); pre-assembling a first turbine unit (33') and a second turbine unit (33"), each comprising: a half-...
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WO/2018/001651A1 |
A turbine (1) comprises: - an outer casing (12), - a plurality of nozzle blades (16), - a plurality of stator blades (18), - a nozzle valve casing (14) supporting the plurality of nozzle blades (16), the nozzle valve casing (14) being fi...
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WO/2018/005886A1 |
An annular duct including a modular annular heat exchanger for a gas turbine engine is provided, where the modular annular heat exchanger includes a plurality of radial modules in circumferentially adjacent arrangement. Each radial modul...
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WO/2018/004583A1 |
A stator vane assembly (10) for a gas turbine engine includes a first endwall segment (12) and a second endwall segment (14) arranged circumferentially spaced from each other, whereby a mate face gap (20) is defined between a first mate ...
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WO/2018/004097A1 |
The present invention relates to: a transition piece assembly having improved cooling efficiency for cooling a high-temperature region formed on the side surface of a transition piece; and a combustor including the same, and provides a t...
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WO/2017/221839A1 |
The present invention pertains to a variable nozzle vane for a variable-capacity turbocharger, wherein: the variable-capacity turbocharger is provided with a scroll flow channel formation part that forms a scroll flow channel toward the ...
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WO/2017/220646A1 |
Static blade (32) for an axial flow turbine comprising an aerofoil portion (44) having a leading edge (44a), a trailing edge (44b), a pressure side and a suction side and radially inner and outer reinforcement portions (46, 48) integral ...
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WO/2017/220881A1 |
Method for testing the integrity of a fluid flow regulating system for a turbomachine, the system comprising a fluid passage pipe (15) associated with a movable throttle; an actuator (21) comprising a movable actuating element, suitable ...
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WO/2017/213113A1 |
Corrosion resistance is enhanced while ensuring high enough heat shielding performance and erosion resistance. The present invention is provided with: a highly porous layer (6) that is formed on a heat-resistant substrate (100), that is ...
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WO/2017/203126A1 |
The present application describes a casing (10), in particular an exhaust casing, for a turbomachine, comprising an inner hub (14) having an axis (A) of rotation and an outer annular ferrule (16) extending around the hub (14), said ferru...
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WO/2017/203151A1 |
The present application concerns a method for manufacturing a casing (10'), in particular an exhaust casing, for a turbomachine, comprising the steps consisting of: a) producing casing sectors (30a), each casing sector (30a) comprising a...
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WO/2017/204941A1 |
The low pressure turbine includes a rotor, an outer casing, a plurality of stages of rotor blades, and a plurality of stages of stator vanes. The rotor includes a longitudinal centerline. The outer casing circumscribes the rotor. The plu...
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WO/2017/202400A1 |
The invention relates to a turbine casing (1) for a turbine (22), in particular a micro gas turbine (21), and to a turbine (22) having such a turbine casing (1). The turbine casing (1) comprises a support ring (2) and a ring contour comp...
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WO/2017/200644A1 |
An apparatus and method of cooling a rotatable member, in particular the rotor of a gas compressor forming part of a gas turbine, enclosed within a casing are provided. The gas compressor includes a rotor (234), a plurality of stages of ...
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WO/2017/200670A1 |
The present disclosure is directed to a shroud assembly for a gas turbine engine that includes a first shroud segment, a second shroud segment spaced from the first shroud segment, and a third shroud segment spaced from the first shroud ...
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WO/2017/195782A1 |
This stator blade (14) is disposed on an inner peripheral surface (11a) of a casing (11) which rotatably supports a rotor (12), and comprises a forward edge (21) which connects a tip surface (14a), which is supported on the inner periphe...
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WO/2017/194860A1 |
A turbine ring assembly comprises a plurality of ring sectors (10) made of a ceramic matrix composite material and forming a turbine ring and a ring support structure (3) comprising a first and a second annular flange (32, 36). Each ring...
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WO/2017/194865A1 |
Assembly (2) comprising an annular turbine distributor (3) for turbomachinery (1), an annular structural element (4) of the turbomachinery (1), coaxial with the distributor (3) and at least one device (5) for attaching the annular distri...
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WO/2017/194886A1 |
The present invention relates to a composite part comprising at least: - a fibrous reinforcement comprising silicon carbide fibers having an oxygen content of less than or equal to 1% as an atomic percentage, and - a matrix present in th...
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WO/2017/194237A1 |
The invention relates to a turbine for an exhaust gas turbocharger having a housing having two exhaust gas volutes, between which a separating wall is provided and which have a common waste-gate opening. The turbine housing is equipped w...
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WO/2017/190884A1 |
The invention relates to a turbine housing (21) for a turbocharger (1) of an internal combustion engine, comprising - an annular duct (22) for guiding an exhaust gas mass flow (AM) to a turbine wheel (12) that can be arranged in the turb...
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WO/2017/192147A1 |
A gas turbine engine has a flow metering device located between the combustor and the transition duct. The flow metering device engages the transition duct with a spring device. The flow metering device meters the airflow and axially cen...
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WO/2017/191075A2 |
A turbomachine component, such as a blade or a vane, is presented. The turbomachine component has an aerofoil. The aerofoil includes a suction side wall and a pressure side wall bordering an aerofoil cavity. The turbomachine component ha...
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WO/2017/190978A1 |
A gas turbine section with improved strut design A gas turbine section for an annular gas path is presented. The annular gas path is defined through a gas turbine engine. The gas turbine section includes an inner and an outer gas path wa...
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WO/2017/187093A1 |
The invention relates to a double-flow turbomachine (26) having an upstream fan wheel (36) and a downstream rectification unit (24) for an air outflow from a secondary annular air stream which is delimited radially on the inside by a rad...
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WO/2017/188040A1 |
The present invention reduces pressure loss in cooling air that is supplied to turbine stator blades. The present invention comprises: a cooling device (7) that generates cooling air by extracting and cooling compressed air (P) from a co...
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WO/2017/186481A1 |
The invention relates to a cooling fluid distributor for distributing cooling fluid in a cavity of a turbomachine blade, having at least two partial inserts (3, 5), wherein the partial inserts (3, 5) are introduced individually into the ...
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WO/2017/187091A1 |
To facilitate the removal of a bearing housed in an arm of a turbomachine casing, which bearing guides a transmission shaft of the turbomachine, the invention provides a casing arm (50) comprising a body (100) consisting of a vertical po...
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WO/2017/182423A1 |
The invention relates to a guide vane (1) for a fluid flow machine, in particular gas turbine, having an outer platform (2) in the properly mounted state of the guide vane, a vane leaf (6) projection from the outer platform (2), which ex...
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WO/2017/182322A1 |
Guide vane (1) for a turbomachine having, in the properly installed state, an outer platform (2), a blade airfoil (3) protruding from the outer platform, extending in a longitudinal direction and defining a cavity (4) in its interior, an...
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WO/2017/176186A1 |
The present invention relates to a turbine arrangement driven by exhaust gases from a combustion engine (2). The turbine arrangement comprises a turbine housing (7), a turbine wheel (6) rotatably arranged in the turbine housing (7), a fi...
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WO/2017/169537A1 |
A dehydrogenation processing method for turbine blades in a steam turbine, said method having a step in which heating steam is supplied to the steam turbine casing when a steam turbine plant is started up or is stopped, thereby heating t...
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WO/2017/168647A1 |
Provided is a fixed vane turbo charger, comprising: a housing including an impeller, an impeller housing space that houses the impeller, a scroll flow passage that is formed on the outer peripheral side of the impeller, and a communicati...
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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/2017/164258A1 |
A structure for supporting turbine nozzles (13) and shrouds (21) opposing rotor blades adjacent to the nozzles by means of a turbine casing (23) covering a turbine (5) in a gas turbine. The front and back end parts of a circumferential f...
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