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WO/2016/047432A1 |
A seal member (7) is provided between a burner arranged around a rotor shaft and a stator vane that is arranged axially downstream and that demarcates a part of a combustion gas flow path (Pg) through which a combustion gas (G) flows. Th...
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WO/2016/047237A1 |
A sealing structure comprises: a first member disposed to face a combustion gas channel; a second member; a third member disposed on the outside of the combustion gas channel; a heat resistant covering portion formed on the combustion ga...
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WO/2016/041814A1 |
The invention relates to a shaft seal (SHS) for sealing off a gap (G) of a feedthrough (PT) for a shaft (S) through a housing (C), wherein these sealing surfaces are located opposite one another in a sealing plane (SEP), wherein the seal...
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WO/2016/034822A1 |
The invention relates to a blade having a platform (14) comprising at least one bumper (40) which rises, on the inner face, from a junction to an intermediate area of the blade, located along a longitudinal axis of the blade, between the...
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WO/2016/034804A1 |
The invention relates to a rotational assembly for a turbine engine, especially a turbine of a helicopter turbine engine, comprising: a rotor provided with at least one impeller wheel (11); a stator ring (21) surrounding the impeller whe...
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WO/2016/036382A1 |
A transition-to-turbine seal assembly is provided. Seal members (52, 58) may include one or more anchoring tabs (54, 60) affixed only to an associated transition (56) and not to a neighboring transition (57). Thus, seal members (52, 58) ...
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WO/2016/030632A1 |
Turbomachine member ring supports (19) extending over sectors of a circle can be constructed from at least one thick flat metal sheet that is curved and welded to form a cylindrical shroud and then formed by pressing into a conical shrou...
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WO/2016/030845A1 |
A turbine (1) of an Organic Rankine Cycle ORC, comprising a shaft (4) supported by bearings (8) and a plurality of mechanical seals (10, 11, 18, 21) arranged around the shaft for confining the operating fluid expanding in the turbine, is...
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WO/2016/030847A1 |
A turbine (1) of an Organic Rankine Cycle ORC, comprising a shaft (4) supported by bearings (8) and a plurality of seals (10, 11) arranged around the shaft (4) for confining the operating fluid expanding in the turbine, is described. The...
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WO/2016/033465A1 |
A turbine blade (10) includes an airfoil (12) extending span-wise along a radial direction, and a shroud (26) positioned along a tip (22) of the airfoil (12) extending generally along a circumferential direction, scalloped, across a pres...
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WO/2016/028310A1 |
A shroud cooling system (100) configured to cool a shroud (50) adjacent to an airfoil within a gas turbine engine (10) is disclosed. The turbine engine shroud (50) may be formed from shroud segments (34) that include a plurality of cooli...
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WO/2016/024060A1 |
A turbomachine module, comprising a mobile wheel rotatably mounted inside a housing of the module and surrounded by a sectorised sealing ring (18) that comprises an annular row of sectors, each ring sector comprising at least one circumf...
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WO/2016/022136A1 |
An interstage seal system (10) for adjusting the position of an interstage seal during operation of a gas turbine engine (14) to increase efficiency of the seal (12) is disclosed. The interstage seal system (10) may include a interstage ...
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WO/2016/021330A1 |
This stator blade (18), which has airfoil sections (19) that extend in a radial direction and an outer shroud (20) that is disposed on the outer side of the airfoil section (19) in the radial direction, is supported inside a casing by me...
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WO/2016/022138A1 |
A compressor (10) configured for use in a gas turbine engine (12) and having a rotor assembly (14) with a pumping system (16) positioned on a rotor drum (18) to counteract reverse leakage flow at a gap (20) formed between one or more sta...
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WO/2016/016048A1 |
The invention relates to a machine comprising: a shaft (2) having a stage (3) such that a first shaft section (9) having a first diameter (11), a second shaft section (10) having a second diameter (12) that is shorter than the first diam...
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WO/2016/016632A1 |
A blade monitoring system and method for a turbine assembly comprising rotating blades (14), the system comprising at least one sensor (10, 12) for transmitting a signal towards said rotating blades and detecting a time-varying return si...
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WO/2016/012237A1 |
The present invention relates to a sealing device for sealing a rotatable shaft (26) of a gas compressor (3) and/or of a gas expander (11), comprising a first sealing chamber (51), which surrounds the shaft (26) and has an inlet (44) for...
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WO/2016/014057A1 |
A stator assembly (10) for a gas turbine engine (12), comprising: a plurality of stator vanes (20), each formed from a generally elongated airfoil (34) having a leading edge (36), a trailing edge (38), a pressure side (40), a suction sid...
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WO/2016/010663A1 |
Some embodiments of the invention are directed to an elliptical sealing system for use with a rotor and a stator housing of a rotary machine. The elliptical sealing system includes a plurality of sealing segments; and an abradable coatin...
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WO/2016/008736A1 |
The present invention relates to a turbine having an inner case, an outer case, an annular cavity defined between said inner case and said outer case, and a plurality of guide vanes which are arranged in said annular cavity, each guide v...
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WO/2015/197942A1 |
Method for repairing a turbomachine component such as a vanes assembly (D), this component comprising an annular wall for supporting an abradable ring (C2), the method comprising steps of initial repair (I) consisting in: removing a firs...
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WO/2015/199153A1 |
In this labyrinth seal device (15) for an axial-flow turbine (5), a labyrinth member (22) forming a gas labyrinth seal (GL) with a turbine disk (6) is fixed to a bearing stand (2) so as to adjoin an exhaust gas outlet casing (12) with a ...
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WO/2015/197626A1 |
Subject matter of the invention is turbomachine which comprises a stator with at least one stator component and a rotor with at least one rotatable rotor component. The stator component defines at least one wall of a cooling cavity with ...
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WO/2015/197980A1 |
The invention relates to a rotary assembly for turbomachine, comprising: a disk (16) having an external periphery exhibiting an alternation of pockets (22) and of teeth (20), vanes (14) extending radially from the disk (16), the roots (2...
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WO/2015/193269A1 |
The invention relates to a fluid energy machine (FEM) and to a method for operating said machine, wherein a tandem dry gas seal (TDGS) comprises an inner seal (SLI) and an outer seal (SLO), wherein the outer seal (SLO) has a first sealin...
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WO/2015/195238A1 |
An aft hub sealing assembly (260) for a gas turbine engine (100) is disclosed. The aft hub sealing assembly (260) includes an aft hub (230), a bearing cap (290), an aft baffle (270), a first seal (264), and a second seal (266). The aft h...
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WO/2015/191174A1 |
A shroud hanger assembly (30) or shroud assembly is provided for components which may be formed of materials having differing coefficient thermal expansion. The assembly includes a multi- piece hanger (32) including a shroud (50) positio...
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WO/2015/191185A1 |
A shroud hanger assembly (30) or shroud assembly (30) is provided for a gas turbine engine wherein a hanger (32) includes a radially depending and axially extending arm. The arm (45) or retainer (60) engages a pocket (56) formed in a shr...
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WO/2015/191186A1 |
A shroud hanger assembly (30) is provided for hangers (34) and shrouds (50) defining dimensionally incompatible components such as those which are press or frictionally fit to engage one another. The shroud hanger assembly (30) includes ...
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WO/2015/191220A1 |
A turbine operable with a first fluid and a second fluid is provided. The turbine includes a shaft and having a dry gas seal area, a balance area, and a shaft surface. The turbine also includes a stationary component coupled to a housing...
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WO/2015/185860A1 |
The invention aims to provide a rotor for a turbine engine comprising: a disc having cavities on the periphery thereof, referred to as primary cavities; a plurality of blades (100) each having a root (110) consisting of, at the bottom po...
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WO/2015/185384A1 |
A method (100, 200) manages a gas turbine assembly during start up or shut down, the gas turbine assembly (10) including a twin shaft gas turbine (5) comprising an input shaft (13) and an output shaft (21) and a speed sensor (40) for mea...
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WO/2015/185382A1 |
The present invention relates to a method for assembling a stator stage (10) of a gas turbine engine (12), comprising: Inserting an adjustment pin (30, 30a, 30b, 30c, 30d) into the through hole (26), wherein the adjustment pin (30, 30a, ...
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WO/2015/185857A1 |
The present invention relates to a method for dimensioning a turbomachine comprising a casing and a disc to which at least one blade is secured, said disc being rotationally driven by a shaft about a turbomachine axis (z), comprising: - ...
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WO/2015/180868A1 |
The invention relates to a steam turbine system (1) comprising a steam turbine (2) which has a turbine housing and at least one turbine shaft (6, 7) accommodated in the turbine housing and sealed by means of seals (8) with respect to thi...
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WO/2015/181489A1 |
The invention proposes an assembly (1) comprising: an exhaust casing (20), rotating about an axis (X-X), comprising a flange (23) for attachment to a mounting (42); a sealing plate (30) for rotation about the axis, the plate being added ...
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WO/2015/180946A1 |
Subject matter of the invention is a turbomachine as well as a use of the turbomachine. The turbomachine, for instance a gas turbine or a steam turbine, comprises a stator with at least one stator component, a rotor with at least one rot...
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WO/2015/181326A1 |
A sealing device (1) is described, for separating a first compartment (3) from a second compartment (5) in a turbomachine, a wet gas being processed in the first compartment. The sealing device comprises a rotary component (7) and a stat...
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WO/2015/176830A1 |
The invention relates to a steam turbine (1) having a turbine housing (2), a rotor shaft (4) which protrudes into the interior of the turbine housing (2), at least one sealing shell (6) which is arranged in a sealing shell receiving area...
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WO/2015/177429A1 |
The invention relates to a turbine rotor for a gas-turbine engine, said rotor including: an upstream turbine disc (1); a downstream turbine disc (5); an annular flange (b); a first shroud (11) connecting the upstream turbine disc to the ...
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WO/2015/176882A1 |
The invention concerns an angle ring connection, that can be dismantled, for sealing the connection between a valve and a turbine housing, wherein a first threaded ring (26) and a second threaded ring (30) are used, being designed, with ...
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WO/2015/173312A1 |
The component of the turbomachine comprises:a body (406) of the component, a bond layer (404) covering a base surface of the body (406), and a top layer (402) covering the bond layer (404) and made of abradable ceramic material; the base...
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WO/2015/175042A2 |
A blade outer air seal according to an exemplary aspect of the present disclosure includes, among other things, a body to be distributed circumferentially about a blade array. The body has a plurality of grooves, which can, for example, ...
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WO/2015/170230A1 |
The present invention relates to a radial turbomachine, comprising: a fixed casing (6); at least one rotor disc (2,2') installed in the casing (6) and rotatable in the casing (6) around a respective rotation axis (X-X); a plurality of an...
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WO/2015/158542A1 |
The invention relates to a wheel disc (1) with at least one sealing metal sheet (2), which is fixed to the wheel disc (1) in a movable manner in the circumferential direction of the wheel disc, and with at least one securing device (6), ...
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WO/2015/155442A1 |
The invention relates to a turbine engine compressor (10'), comprising at least one annular row of variable-pitch stator blades (12), wherein said blades are substantially radial and comprise pivots (22, 24) at the radial ends thereof, t...
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WO/2015/156810A1 |
A gas turbine engine (1) includes a control system to adjust clearance between rotating and stationary components, with a turbine blade section having multiple rows of stationary and rotatable blades (34, 37) positioned about a rotor (8)...
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WO/2015/152742A1 |
A turbine or turbine system includes a compressor, a combustor, a turbine section, a diffuser with a parting line between two components, and a seal along the parting line. The seal includes a protrusion, a recess, and a flexible portion...
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WO/2015/153171A1 |
A gas turbine engine includes a conduit that is configured to direct a fluid to at least one manifold that is adjacent to a turbine section. A first intake is in fluid communication with the conduit. A second intake is in fluid communica...
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