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Matches 1 - 50 out of 8,145

Document Document Title
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/2017/007529A1
A turbine engine duct assembly and joint assembly having an outer shroud at least partially defining an interior of the joint assembly, an inner shroud at least partially received within the outer shroud and forming an interface therewit...  
WO/2017/005781A1
A method of manufacturing a vane (61), the vane (61) comprising a root part (62), an aerofoil (74) and a cooling channel (63) extending through at least the root part (62), the cooling channel (63) is defined by a wall (76) and comprises...  
WO/2017/003421A1
An arrangement (14) including: a wall (34) having raised ribs (36) defining a perimeter (66) and a plurality of pockets (52) within the perimeter; a stud (100) extending from the wall into a respective pocket; a cover sheet (12) disposed...  
WO/2017/003455A1
A turbine stator vane (10) having a cooling circuit (62) formed within the vane (10) including a plurality of channels, at least a first pass channel (12), a second pass channel (14), and a final pass channel (16) and an inter-stage purg...  
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/2016/193589A1
The invention relates to an annular wall of a turbine engine combustion chamber, including between a cold side (16a, 18a) and a hot side (16b, 18b), a plurality of air-inlet openings (30) distributed according to at least one circumferen...  
WO/2016/190760A1
A flow mixing lobe (54) for an exhaust diffuser (30) includes a first flange member (64) having a first leading end (72), a first trailing end (73), and an intermediate portion (74) extending therebetween. A second flange member (65) inc...  
WO/2016/189234A1
Turbine engine unit for lubricating a bearing holder A turbine engine unit is provided, including: an inter-turbine housing that includes a hub (1) including a bearing holder, a ferrule (2) extending around and at a distance from the hub...  
WO/2016/189612A1
Provided are: a niobium silicide-based composite material which achieves a good balance between toughness and mechanical characteristics in an ultra-high temperature range (at 1,200°C or higher) at high levels; a high-temperature compon...  
WO/2016/188855A2
A silicide-based composite material is disclosed, comprising a silicide of Mo, B, W, Nb, Ta, Ti, Cr, Co, Y, or a combination thereof, Si3N4, and at least an oxide, as well as and a process for producing the same.  
WO/2016/184549A1
The invention relates to a radial compressor (10), in particular for an exhaust gas turbocharger of an internal combustion engine, comprising at least one housing part (12) by means of which a receiving chamber (14) for a compressor whee...  
WO/2016/184617A1
The invention relates to an exhaust-gas turbocharger (1), comprising a turbine housing (2) having two exhaust volutes (3, 4), which are separated from each other by a separating wall (5), and comprising two spiral tongues (6, 7), each of...  
WO/2016/180697A1
The invention relates to a compressor (10) for compressing a working medium, comprising at least one rotor-side rotor-blade ring (12, 13) and at least one stator-side guide-vane ring (15, 16), wherein the or each rotor-blade ring has a p...  
WO/2016/177705A1
The invention involves a conduit connection assembly comprising a first conduit part (201) and a second conduit part (401), adapted to be assembled to form a conduit connection delimiting a first fluid conducting volume (VI), characteriz...  
WO/2016/178664A1
An improved layout of cooling fluid conduits in a turbine transition duct is provided. The transition duct (10) may include a transition body made with a multi-panel arrangement (12, 14) that defines a passage to route a hot combustion g...  
WO/2016/177644A1
There is disclosed a turboshaft engine (10) having a principal rotational axis and comprising a power turbine (16), a tail bearing housing (18) and an exhaust collector (19) arranged in axial flow series along said axis. The tail bearing...  
WO/2016/177881A1
The invention relates to a method and apparatus for assembling nozzles 31 between buckets 41,42 of a turbine, particularly a gas turbine, in which a temporary fixing of the nozzles 31 to the buckets 41,42 during the assembly is provided.  
WO/2016/177430A1
The invention involves a conduit connection assembly, characterised in that the assembly comprises a first conduit part (201) and a second conduit part (401), adapted to be assembled to form a conduit connection delimiting a fluid conduc...  
WO/2016/173920A1
The invention relates to a hot gas-conducting casing (7) comprising a hot gas duct (8) of annular cross section, wherein the hot gas duct (8) is bounded inwardly by a casing inner wall (9) and outwardly by a casing outer wall (10) provid...  
WO/2016/170114A1
A turbomachine airfoil component (15) is disclosed, having a leading edge (15L) and a trailing edge (15T). The airfoil component comprises a hole (21) extending from an inlet (21A) positioned at the leading edge (15L) towards the interio...  
WO/2016/170165A1
The gas turbine engine (3) comprises a compressor section (9) configured for compressing combustion air, a combustor section (15) and a turbine section (21). The turbine section (21) comprises a turbine rotor (41) with a bladed wheel (43...  
WO/2016/168425A1
A gaseous fuel introducer comprising a first mounting surface shaped and located to couple to a first wall of a charger; a first input, the first input being an air input; a second input, the second input being a gaseous fuel input; and ...  
WO/2016/162105A1
The invention relates to a controller for an exhaust gas conductive portion, through which a flow can pass, of a turbocharger. The controller (13) is designed to open and close a bypass channel (11) in the exhaust gas conductive portion ...  
WO/2016/162249A1
A blade (51) and an assembly tool (87) for assembling a blade set to a rotor disc (35) is disclosed. The blade (51) comprises a root portion (50), an aerofoil (54) and a shroud (56), the root portion (50) has two lateral sides each defin...  
WO/2016/164332A1
An integrated fan heat exchanger stator assembly is provided including a hub and a casing. A plurality of elements is arranged between the hub and the casing. The plurality of elements is separated from one another by a plurality of exte...  
WO/2016/162106A1
The invention relates to a regulating device for an exhaust-gas-conducting section of an exhaust-gas turbocharger, wherein the regulating device (19) is designed for guiding a flow of a fluid into a bypass duct (22), which is formed in t...  
WO/2016/164661A1
The invention relates to an exhaust gas supply arrangement (1) to a turbine wheel (11) of an exhaust gas turbocharger (2), having a flange (14) for connecting to a manifold (3) of an 5 internal combustion engine (4), an exhaust gas suppl...  
WO/2016/156200A1
The present invention relates to a vane device (100) for a gas turbine. The vane device (100) comprises: an inner shroud (110) and an outer shroud (120), an aerofoil (101, 115) arranged between the inner shroud (110) and the outer shroud...  
WO/2016/156211A1
The invention relates to a guide vane assembly (1) comprising at least partially resilient brackets (25; 31; 34), each of which has some tolerance between a web (7) of a guide vane (4) and an inner ring (3) of the guide vane assembly (1)...  
WO/2016/156744A1
The invention relates to an oil jet (10) for a turbine engine, comprising a body (16) including a circulation pipe (18) intended for the flow of a pressurised fluid. The body (16) of the jet (10) comprises a first portion (24) and a seco...  
WO/2016/156743A1
The invention relates to a turbine engine which comprises at least one stator bladed sector (10) and a fluid distribution circuit (22), the stator bladed sector comprising at least one blade (12), a fluid intake (25a), a fluid outlet (25...  
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/2016/155923A1
The present invention relates to a transition duct assembly (1) comprising a plurality of transition ducts (2), each transition duct (2) having a tubular main body (3) and a flange portion (4) provided at a downstream end of said tubular...  
WO/2016/158533A1
A support device is provided with: a support member having a body disposed in a recess provided in the upper surface of the lower half of an outer member, the support member further having a protrusion provided on the body, the protrusio...  
WO/2016/152573A1
A blade having a flow path forming plate (60o) that defines a portion of a combustion gas flow path. Multiple rear passages (75) opening at a rear end surface (62b) are formed in the flow path forming plate (60o). The opening density of ...  
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/2016/142631A1
The invention relates to an element of a stator guide of an axial compressor of a turbomachine, in the form of a monobloc assembly, the outer shape thereof being a cylinder sector forming, in a radially outer manner, an outer shroud sect...  
WO/2016/139574A1
Expansion turbine (100) for a working fluid in an organic Rankine cycle, comprising a housing (21), at least one inlet duct (10) for working fluid feeding and an outlet duct (20) for working fluid discharge, at least one statoric group (...  
WO/2016/134907A2
The invention relates to a stator or rotor blade device (1) which is cast from a metal alloy and comprises at least one blade base (3) and an airfoil (4) designed as one piece with the blade base (3), a hollow space (6) extending from th...  
WO/2016/134907A3
The invention relates to a stator or rotor blade device (1) which is cast from a metal alloy and comprises at least one blade base (3) and an airfoil (4) designed as one piece with the blade base (3), a hollow space (6) extending from th...  
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/2016/129949A1
The present invention relates to an axial flow turbine, comprising: a rotor mounting part; a housing having a fluid supply part surrounding the rotor mounting part; a rotor which is installed at a rotation shaft installed in the housing ...  
WO/2016/129375A1
This gas turbine component comprises a metal intermediate structure (110) and a ceramic layer (130). A gas path surface (102) which faces toward a combustion gas flow path (GP) side in a radial direction (Dr), and a pair of side surfaces...  
WO/2016/127241A1
A two-way flow control device including: a housing defining a first opening interface and a second opening interface, a rotor having a plurality of blades, each blade controllable to be angled in a range of positive and negative blade an...  
WO/2016/128665A1
The invention relates to a turbine engine assembly comprising an air flow guide assembly, including at least one guide vane (21) and at least one structural arm (30), said vane and arm extending radially about an axis (X-X). The arm incl...  
WO/2016/129588A1
Provided is a coated member which is provided with a heat shielding coating layer that exhibits excellent characteristics in a high temperature environment in which water vapor is present. A coated member (100) which is provided with a h...  
WO/2016/128664A1
The invention relates to a turbine engine air flow guide assembly including: a structural arm (30); and a guide vane (21) on the lower surface of the structural arm, comprising a leading edge (22), a trailing edge (23), and a camber line...  
WO/2016/124853A1
The invention relates to a plug (50) for preventing corrosion of an attachment opening (22). Said plug comprises: - a bottom surface (51) including an opening (60) for receiving a head (27) of a tightening means (23); - a top surface (52...  
WO/2016/121163A1
A turbine blade provided along the radial direction of a turbine is provided with an airfoil part positioned inside a fluid channel of the turbine, and a shroud part positioned on the inner side or outer side of the airfoil part in the r...  

Matches 1 - 50 out of 8,145