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Matches 1 - 50 out of 8,292

Document Document Title
WO/2017/069145A1
In the present invention the end plate (60) of a blade (50) has a gas path surface (61) facing a combustion gas flow passage (49) side, an end surface (63) along the edge of the gas path surface (61), multiple passages (81p), and a baseb...  
WO/2017/063786A1
The present invention relates to a method of manufacture of a channelling tube (10). The tube is realised by rolling a metal sheet (16) in order to obtain a tube having a spiral cross section. A gap (44) is defined between two ajacent la...  
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/2017/058694A1
A spiral cooling system for cooling an aft turbine casing of a gas turbine engine. The gas turbine engine includes a turbine casing having a fore end and an aft end, a star bearing support member supporting a bearing housing and includin...  
WO/2017/058155A1
Provided is a way of implementing impingement cooling for a gas turbine engine. Instead of welding the impingement sheets (10a-10i) to an integrated exit piece (15), the impingement sheets (10a-10i) are attached in a way that takes advan...  
WO/2017/051346A1
This disclosure describes an improved method of electron beam ("EB") welding utilizing a collection pocket (118). The method includes providing a first surface (110,146) and a second surface (100,132,140,144), forming a collection pocket...  
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/2017/046534A1
The invention relates to a nozzle sector (22) for a turbine engine. The nozzle sector comprises a radially outer platform (24), a radially inner platform (26), a first end blade (81), a second end blade (84) and at least one first centra...  
WO/2017/047516A1
The objective is to enable the portion of a combustor tube where the temperature rises to be cooled efficiently, and to improve the reliability of a combustor tube without reducing the efficiency of a gas turbine. Therefore, this combust...  
WO/2017/048149A1
The invention relates to the energy sector. A device for converting the energy of a drop in the pressure of a gaseous working fluid comprises a housing, a consumer of the mechanical energy generated, and an expansion turbine with a blade...  
WO/2017/042448A1
Casing for rotary machines, in particular for turbomachines, comprising a chamber (2) intended to house a turbine, and a gas circulation duct (3) opening into said chamber, the casing having at least one cavity (4) surrounding at least p...  
WO/2017/039567A1
A combustor transition duct (110) comprising a main duct portion (113) having a primary opening and a secondary opening, wherein a first axis extends from a center of the primary opening to the secondary opening; an extension flange (115...  
WO/2017/037399A1
The invention relates to a part (1) or an assembly of parts of a splitter stage of a turbofan, comprising a plurality of obstacles (4, 5, 6a, 6b) including at least one a blade (4) and at least one arm (5, 6a, 6b), and a platform (2) fro...  
WO/2017/029689A1
The turbine (21) is equipped with: a casing (30); a turbine rotor (90) which is disposed inside the casing (30) so as to penetrate therethrough; rotor vanes (100) which are implanted along the circumference of the turbine rotor (90); an ...  
WO/2017/029090A1
The invention relates to a tubular combustion chamber (22) for a gas turbine (1), comprising at least one burner arrangement (11), a housing wall (24) which surrounds the combustion chamber interior and has a flame tube (20) and a transi...  
WO/2017/025995A1
A turbine blade (120), a plurality of which are arranged in a row in an annular flow path in an axial-flow turbine, is provided with: a dorsal surface (106) which curves in a convex shape; a ventral surface (107) on the opposite side to ...  
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/2017/023325A1
A trailing edge duct (110) is used with gas turbine engines. The trailing edge duct (110) is unitary in shape and has improved aerodynamics. The trailing edge duct (110) has a trailing edge (120) that is able to provide improved support ...  
WO/2017/021067A1
The invention relates to a turbomachine, in particular a steam turbine (2) having an overload inflow region (17) which is designed for the inflow of overload steam, wherein said overload steam is prevented from impinging on the rotor sur...  
WO/2017/023328A1
A gas turbine engine component (10), having: a base layer (60) including an array (110) of pockets (52) separated by raised ribs (36), and a film cooling hole (70) through the base layer in each pocket; and a cover sheet (62) diffusion b...  
WO/2017/023327A1
A combustor has a trailing edge duct (110) that has cooling features located at various locations. The cooling features comprise pockets (125) that have pocket channels (127) which extend from the pockets (125) to seam locations on the m...  
WO/2017/023330A1
A ducting arrangement (10), including: an annular duct (38) having a plurality of discrete IEPs (18) secured together to form the annular duct that defines an annular chamber (14) configured to deliver an annular flow of combustion gases...  
WO/2017/023326A1
A combustor has a trailing edge duct (110) that has a trailing edge (120) that is adapted to be connected to an adjacent trailing edge (120) of a trailing edge duct (110). The connections between the adjacent trailing edges may be formed...  
WO/2017/023331A1
A ducting arrangement (10), including: an annular duct (38) having a plurality of discrete integrated exit pieces (IEP 18) secured together to form the annular duct and an annular chamber (14) configured to deliver an annular flow of com...  
WO/2017/017392A1
The proposed invention is an air-flow straightening assembly for a turbine engine comprising: - a cylindrical platform (15) centred on an axis (X-X), - at least one straightener blade (20) extending from the platform, - a structural arm ...  
WO/2017/015746A1
A mid-turbine frame module comprises an outer structural ring, an inner structural ring and a plurality of circumferentially spaced-apart spokes structurally interconnecting the inner structural ring to the outer structural ring. At leas...  
WO/2017/015747A1
A mid-turbine frame module comprises an outer structural ring, an inner structural ring and a plurality of circumferentially spaced-apart spokes structurally interconnecting the inner structural ring to the outer structural ring. The spo...  
WO/2017/017708A1
Provided is a cobalt-base alloy member having improved oxidation resistance at high temperature. This method for producing a cobalt-base alloy member includes a step for preparing a cobalt-base alloy on which an aluminizing treatment has...  
WO/2017/015743A1
An integrated strut and turbine vane nozzle (ISV) comprising: inner and outer duct walls defining a flow passage therebetween, an array of circumferentially spaced-apart struts extending radially across the flow passage, and an array of ...  
WO/2017/018982A1
An improved gas turbine combustion system having a reduced combustion residence time in a combustion turbine engine is provided. The combustion system includes a flow-accelerating structure (16, 51), such as a transition duct, having an ...  
WO/2017/013356A1
The invention relates to an exhaust casing for a turbine engine of an aircraft, including: a collar (4), a hub (5), hollow arms (63) connecting said collar (4) to said hub (5), and an opening piece (3) which is located on the collar (4) ...  
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...  
WO/2017/013354A1
The invention relates to distributor blading (10) having a blade (12), including a pressure-side wall (16) and a suction-side wall (14), and an insert (20) placed in the blade (12) and including: a closed wall (22) having an outer skin (...  
WO/2017/013361A1
The invention relates to an aircraft comprising a fuselage (1) and a propulsion assembly, said propulsion assembly comprising at least one fan rotor (7, 8) located at the rear of the fuselage (1) in the extension thereof along a longitud...  
WO/2017/012686A1
The invention relates to a turbine (38) for a turbocharger of an internal combustion engine (10), comprising a turbine housing that has a receiving area, in which a turbine wheel (40) can be received in a rotatable manner about a rotatio...  
WO/2017/010671A1
The present invention relates to a steam turbine reducing unnecessary axial force, which can be applied to a turbine shaft transmitting the rotational driving force of a plurality of nozzle rotating bodies connected in multiple stages, a...  
WO/2017/010627A1
The present invention relates to a gas turbine that includes a cooling system provided with a cool-air supply path detouring to an outer casing and, more specifically, to a gas turbine that includes a cooling system and a cooling method ...  
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/2016/188855A3
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, from the group consisting of Yttrium oxides and Cerium oxides as well as ...  
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...  

Matches 1 - 50 out of 8,292