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Patent Searching and Data


Matches 1 - 50 out of 7,061

Document Document Title
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)...  
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...  
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...  
WO/2017/069582A1
The present invention relates to a sealing assembly for a turbine, the sealing assembly comprising: a first sealing member disposed on a fixed body of a turbine; and a second sealing member which faces the first sealing member and is dis...  
WO/2017/063826A1
It is described a sealing part (73) for a turbine section (18) of a gas turbine (10) to seal a gap (g) between two circumferentially adjacent rotor blades (64, 70), comprising: a body (71); a coating (69) applied on a surface of the body...  
WO/2017/060604A1
The invention relates to a turbine ring assembly including a plurality of ring sectors (10) forming a turbine ring (1), and a ring support structure (3) including an upstream ring-shaped flange (32) and a downstream ring-shaped flange (3...  
WO/2017/058745A1
A high-efficiency compressor section (10) for a gas turbine engine is disciosed. The compressor section includes a vane carrier (12) adapted to hold ring segment assemblies (16) that provide optimized blade tip gaps (28,29) during a vari...  
WO/2017/058740A1
A high-efficiency compressor section (10) for a gas turbine engine is disclosed. The compressor section includes a vane carrier (12) adapted to hold ring segment assemblies (16) that provide optimized blade tip gaps (28,29) during a vari...  
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 ...  
WO/2017/046499A1
The invention relates to a ventilation device for a turbomachine turbine casing, comprising a plurality of line sets (16') configured to spray air over the turbine casing, the line sets being arranged next to one another, each line set c...  
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...  
WO/2017/043157A1
This optical fiber probe is provided with: a probe main body 21; optical fibers 22 which are accommodated in an internal space S of the probe main body 21 and distal end portions of which are disposed on the side of the probe main body 2...  
WO/2017/043415A1
A seal member assembly structure and assembly method, a seal member, and a gas turbine, wherein, in a state in which a first flange portion (63, 65) of a combustor tail pipe 43 is fitted in a first fitting portion (73, 76) of a seal memb...  
WO/2017/037394A1
The invention relates to a turbine of a gas turbine engine. Said turbine includes a stator sealing ring element (31) arranged so as to form a labyrinth sealing joint in combination with at least one wiper, rotatable about the axis of the...  
WO/2017/033227A1
The steam turbine (1) is equipped with: a rotor shaft (21) which has disk parts (23) fixed to a shaft core part (22) rotating about an axis (Ar); multiple rotor blade cascades (31) which are fixed to the outer peripheries of the disk par...  
WO/2017/026314A1
A shroud of a stationary blade (50) has formed therein a plurality of circumferential ejection passages (95) that connect with a cavity (69) into which cooling air (Ac) flows and that open on a circumferential end surface (63). Of a cent...  
WO/2017/017227A1
The shaft seal arrangement for a rotating turbomachine shaft having a rotation axis, comprises a rotor part (41) and a stationary part (43). Adry gas seal (45) is further provided, in combination with a cooling fluid volume (67) arranged...  
WO/2017/014737A1
A turbine arrangement including a rotor and a stator surrounding the rotor and comprising guide vane segments, each guide vane segment comprising an airfoil (14) and a radially inner vane platform (16). A seal arrangement (30) includes a...  
WO/2017/013326A1
The invention relates to a stage of variable-pitch blades (110) for a turbine engine, each blade including an impeller (114) which comprises: a first radially inner frustoconical surface (150) in which the cone angle is flared radially i...  
WO2017009420A1
The invention refers to a coolable wall element (10) for a gas turbine, comprising a base body (12) having a first surface (14) subjectable to a hot gas, a second surface (16) which is arranged opposite of the first surface and a first s...  
WO/2017/009457A1
The invention relates to a ring segment (10) for a gas turbine, comprising a base body (12) having a first surface (14) subjectable to hot gas, a second surface (16) which is arranged opposite of the first surface (14) and fastening elem...  
WO/2017/007530A1
A turbine engine duct assembly (80) including a joint assembly (86) having an outer shroud (100), a bellows (106), a flared tube (120), a backing ring (122), and a kinematic ring (128). The joint assembly provides for dynamic movement of...  
WO/2017/006045A1
The invention relates to an assembly for a turbine (22) of a turbine engine, comprising a casing (32) and an annular duct (34) surrounding the casing, which can be connected to means for supplying cooling air, and having a radially inner...  
WO/2017/006054A1
The invention relates to a rotary assembly of an aeronautical turbomachine comprising: a fan (2) disc (22) having at least one tooth (25) and at least one platform (30) mounted on the tooth (25) of the fan disc. The tooth of the fan disc...  
WO/2016/207761A1
A turbine of an organic Ranking cycle ORC is described, the turbine comprising a shaft supported by bearings and a plurality of seals arranged round the shaft for confining the operating fluid expanding in the turbine. The seals define a...  
WO/2016/203141A1
A device (21) for coating a surface of an turbomachine annular casing (10), with an abradable layer obtained by polymerising a resin, characterised in that it comprises first support means (22), optionally second automated means (24) mov...  
WO/2016/199319A1
[Problem] To provide a turbine that has a simple structure, that is composed of a CMC and achieves a wide range of gas flow passages while suppressing thermal stress acting on turbine stator blades, and that can consequently realize furt...  
WO/2016/194677A1
A sealing device for minimizing leakage of a fluid flowing through an annular gap between a stationary member and a rotating member of a rotating machine comprises an annular fixed fin provided to the annular gap, and an annular movable ...  
WO/2016/188949A1
Disclosed is a turbocharger comprising an exhaust bypass path, which path has a bypass valve device comprising: a plate-like valve element having a shaft, the shaft of said valve element being movably connected to a valve element support...  
WO/2016/189223A1
The present invention relates to a turbine ring assembly including a plurality of ring sectors (1) made of a composite material having a ceramic matrix forming a turbine ring, and a ring-supporting structure (2) including two annular fla...  
WO/2016/189224A1
The invention relates to a turbine ring assembly which comprises a plurality of ring sectors (10) made of a composite material with a ceramic matrix forming a turbine ring (1) and a ring-supporting structure (3) including two flanges (32...  
WO/2016/189222A1
A turbine ring assembly comprises a plurality of ring sectors (10) made of ceramic matrix composite material, forming a turbine ring (1) and a ring support structure (3) secured to a turbine casing (30) and comprising two annular flanges...  
WO/2016/188524A1
The invention relates to a rotor (1) for an exhaust gas turbocharger (2), having a turbine impeller (5), a radial sealing section (6) which adjoins the turbine impeller (5) on the compressor side and is fixed in rotation with the turbine...  
WO/2016/189215A1
A turbine ring assembly comprises a plurality of ring sectors (10) made from a ceramic matrix composite material forming a turbine ring (1) and a ring support structure (3) comprising two annular flanges (32, 36), each ring sector (10) h...  
WO/2016/185732A1
A guide surface which expands to the outer peripheral side as the guide surface extends from the upstream side to the downstream side is formed on a support section. A guided surface which expands to the outer peripheral side as the guid...  
WO/2016/179608A3
An intershaft seal assembly (30) for use between an inner shaft (32) and an outer shaft (31) rotatable within a turbine engine is presented. The seal assembly (30) includes a sealing ring (33), an inner ring (39), and a pair of end rings...  
WO/2016/179608A2
An intershaft seal assembly (30) for use between an inner shaft (32) and an outer shaft (31) rotatable within a turbine engine is presented. The seal assembly (30) includes a sealing ring (33), an inner ring (39), and a pair of end rings...  
WO/2016/174374A1
The present invention relates to a sealing system for a rotating shaft (10) of a mechanical or electric compressor, the shaft (10) being connected to at least one compartment (1, 2), and comprising at least one seal (5, 5', 6, 6') dispos...  
WO/2016/173793A1
The invention relates to a fluid flow engine (9), in particular compressor or turbine of a gas turbine engine (10), having a stationary engine casing (38) and a rotor assembly (39) rotatable supported in the engine casing (38), the rotor...  
WO/2016/168870A3
An intershaft seal assembly (30) for use between an inner shaft (32) and an outer shaft (31) within a turbine engine is presented. The seal assembly (30) includes a sealing ring (33), centrifugal retaining plates (102), and end rings (37...  
WO/2016/163040A1
The shield member (30) is disposed over a gap between platform parts (20) of adjoining turbine rotor blades (10), is formed from a ceramic-based composite material, and shields the gap between the platform parts (20).  
WO/2016/157127A1
The invention refers to a sandwich arrangement comprising at least two peripheral disposed ceramic panels (101a, 101b) and a ceramic felt (110) which is inserted be- tween a first and second ceramic panel, The material of the first ceram...  
WO/2016/148692A1
A stator assembly (10) usable in a gas turbine engine (12) and configured to restrain inner and outer endwalls (14, 16) to limit deflection, provide mechanical dampening and prevent clearance loss relative to adjacent blade rotor disks i...  
WO/2016/146942A1
The invention concerns a turbine ring assembly comprising a plurality of ring sectors (1) made from ceramic matrix composite material and a ring support structure (2), each ring sector (1) having a part forming an annular base (5) with a...  
WO/2016/146920A1
The invention relates to an assembly for a gas turbine, including stationary vanes forming a distributor (5) in which the adjacent side surfaces (171, 173) are placed end-to-end and which comprise slots (31a, 33a) made facing one another...  
WO/2016/148691A1
A shrouded turbine airfoil (10) with a tapered knife edge seal (12) for weight reduction at the turbine airfoil tip (14) and for enhanced contact is disclosed. The shrouded turbine airfoil (10) may include one or more shrouds (16) attach...  
WO/2016/142982A1
An axial-flow turbine (10) according to an embodiment is provided with: a plurality of heat shield plates (21) that surrounds a turbine rotor (12) via cooling spaces (S1, S2); and a leg part (40) that supports the heat shield plates (21)...  
WO/2016/143230A1
Provided are a sealing device for a gas turbine, a gas turbine, and an aircraft engine, said sealing device being provided with a first sealing section (51), which is provided between a platform (42) of a rotor blade (28) of a turbine (1...  
WO/2016/143657A1
Provided are a divided-type brush seal device, a brush seal piece, and a method for assembling a divided-type brush seal device, with which the brush seal piece can be applied to an attachment section having an allowable range of curvatu...  
WO/2016/137631A1
A non-contacting rotary member seal for a turbomachine is provided. The non-contacting rotary member seal may include an annular seal body having an inner annular surface extending axially from a first axial end to a second axial end. Th...  

Matches 1 - 50 out of 7,061