| Document |
Document Title |
|
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/2017/010627A1 |
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/2017/010671A1 |
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/2017/007530A1 |
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...
|
