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Matches 1 - 50 out of 7,005

Document Document Title
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...  
WO2017009457A1
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...  
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/2017/007530A1
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...  
WO/2016/132966A1
This seal device for a turbine is provided around a rotor so as to separate a high-pressure space and a low-pressure space. The seal device for a turbine is provided with a plurality of thin plates that are arranged along the outer circu...  
WO/2016/133580A1
Turbine engine (80) components, such as blades (92), vanes (104, 106), ring segment 110 abradable surfaces 120, or transitions (85), have vertically aligned engineered surface features (ESFs) (632, 634) and furcated engineered groove fea...  
WO/2016/133581A1
Turbine and compressor casing abradable component embodiments for turbine engines, with composite, tri-angle, "hockey stick" like plan form pattern, abradable surface ridges and grooves. The tri-angle plan form pattern incorporates diffe...  
WO/2016/132646A1
This seal device for a turbine is provided around a rotor so as to separate a high-pressure space and a low-pressure space. The seal device for a turbine is provided with: a plurality of thin plates that are arranged along the outer circ...  
WO/2016/133990A1
An oxide and non-oxide SiC-SiC based ceramic matrix composite ("CMC") component (60) for a combustion turbine engine (20) has a solidified ceramic core (62), with a three-dimensional preform (62A) of ceramic fibers, embedded therein. Eng...  
WO/2016/133583A1
Turbine and compressor ring segment abradable component embodiments for turbine engines vary localized porosity or abradability through use of holes (328A-C) of desired profiles that are formed into monolithic abradable rib structures (3...  
WO/2016/133486A1
A ring segment system (100) for a gas turbine engine (10) is disclosed. The ring segment system (100) may be formed from ring segments (50) that circumferentially surround a rotor assembly (40). The ring segments (50) may each include a ...  
WO/2016/133982A1
Delamination of thermal barrier coatings ("TBC's") (276) from superalloy substrates (262) of components (260) for turbine engines (80), such as engine blades (92), vanes (104, 106), or castings in transitions (85), is inhibited during su...  
WO/2016/133582A1
Turbine and compressor casing ring segment components for turbine engines include abradable surfaces with a zonal system of forward (zone A) and rear or aft sections (zone B) surface features. The zone A surface profile comprises an arra...  
WO/2016/133987A2
Cooling passages (99, 105) are formed in components for combustion turbine engines, such as blades (92), vanes (104, 106), ring segments (110) or castings in transitions (85), during investment casting, through use of ceramic shell inser...  
WO/2016/133579A1
Turbine engine (80) components, such as blades (92), vanes (104, 106), ring segment 110 abradable surfaces 120, or transitions (85), have furcated engineered groove features (EGFs) (403, 404, 418, 509, 511, 512) that cut into the outer s...  
WO/2016/128663A1
The invention relates to a turbomachine nut (118), particularly for axially locking a bearing (110) ring (114), the nut comprising a thread (146) for screwing onto a part of the turbomachine, and locking means (152) for locking the nut a...  
WO/2016/124262A1
The invention relates to a brush seal arrangement (1) for sealing a gap (2) between a rotor (3) and a stator (4). The brush seal arrangement (1) comprises at least one brush seal (5) which has a brush housing (6) and a multiplicity of br...  
WO/2016/121259A1
This turbine is provided with a sealing device (40). The sealing device comprises: at least one step face (42) which is provided in a region of an outer circumferential surface of a rotor (5) facing a shroud (35) of a stator vane (20)in ...  
WO/2016/121740A1
Provided is a brush seal capable of reliably fixing a low-pressure-side plate and a high-pressure-side plate in stable positions. In an annular brush seal (1) in which a brush body (4) having a plurality of wires is held between a low-pr...  

Matches 1 - 50 out of 7,005