| Document |
Document Title |
|
WO/2020/120962A1 |
A seal assembly for use in a turbomachine, the seal assembly comprising an oil seal plate; a rotatable component which defines a central axis and is received in a central aperture of the oil seal plate; and an annular seal which comprise...
|
|
WO/2020/117882A1 |
A turbofan engine assembly includes a fan, a fan case, and a fan case liner. A fan blade has a fan blade tip at the distal end of the fan blade. The fan case liner is spaced apart from the fan blade tip by a clearance distance, is dispos...
|
|
WO/2020/115374A2 |
The invention relates to a device (9) for cooling a turbine casing (7) for a turbomachine, for example an aircraft turbojet engine, which extends about an axis (X) and comprises air distributing means configured to take in air and convey...
|
|
WO/2020/115383A1 |
The invention concerns an air-sealing device (40) intended to be inserted between an aircraft dual-flow turbine engine casing element (16) and a nacelle element (30), the sealing device comprising an attachment tab (42) at the end of whi...
|
|
WO/2020/116155A1 |
A turbine rotor blade that comprises: a base end part that is fixed to a rotor shaft; and a blade part that includes a pressure surface, a suction surface, and a top surface that connects the pressure surface and the suction surface. The...
|
|
WO/2020/112136A1 |
A mid-frame section of a gas turbine engine having a radial clearance adjustability and a method for adjusting a radial clearance to a rotor in a mid-frame section of a gas turbine engine are presented. The mid-frame section includes a r...
|
|
WO/2020/099762A1 |
Assembly (1) comprising a rotor disc (4), an adjacent stator (6) and a plurality of sealing elements (10, 11) secured to said rotor disc (4), said stator (6) comprising an inner platform (9) and a root (32) bearing at least one abradable...
|
|
WO/2020/095470A1 |
Provided is a rotor blade of an axial-flow fluid machine which makes it possible to reduce secondary flow loss in the vicinity of a hub-side end wall, while maintaining the effect of reducing bending stress acting on a blade portion. The...
|
|
WO/2020/094410A1 |
The invention relates to a rotor blade (01) for use in a rotor of a gas turbine having a blade root (02) which is adjoined by a blade platform (03) and has a radially extending blade (04), wherein a sealing groove (07) is arranged on a s...
|
|
WO/2020/089540A1 |
The invention relates to a turbine shroud sector (2) made of ceramic matrix composite, of longitudinal axis X and which comprises a base (3) with a radially internal face (6), a radially external face (7) from which there extend upstream...
|
|
WO/2020/078608A1 |
The invention relates to an exhaust gas turbine (20) of an exhaust gas turbocharger (100) with a wastegate valve arrangement (10), and to an exhaust gas turbocharger (100) with an exhaust gas turbine (20) of this type. The exhaust gas tu...
|
|
WO/2020/074917A1 |
A turbine comprising: a turbine housing, a wastegate passage connecting the turbine inlet and the turbine outlet; and a wastegate valve comprising a movable valve member. The wastegate valve has an open state in which a first gas may pas...
|
|
WO/2020/076298A1 |
A seal assembly (10) for sealing a circumferential gap (11) between a first machine component (38) and a second machine component (40) which is rotatable relative to the first machine component 5 (38) about a longitudinal axis (42). The ...
|
|
WO/2020/076301A1 |
A seal assembly (86) for sealing a circumferential gap (11) between a first machine component (38) and a second machine component (40) which is rotatable relative to the first machine component 5 (38) about a longitudinal axis (42). The ...
|
|
WO/2020/064354A1 |
The invention relates to a sealing arrangement (1) for sealing a gap (2) between a rotatable rotor component (3) and a stationary stator component (4), wherein the sealing arrangement (1) comprises a sealing element (7) which is fluidica...
|
|
WO/2020/065178A1 |
The invention relates to an internal casing hoop (50) for a turbomachine, centered on a longitudinal central axis, which comprises: a main body (51) centered on this axis, with two ends, delimited by surfaces that are radially inner and ...
|
|
WO/2020/065161A1 |
Turbine stator for a turbomachine extending around an axis, the stator comprising a plurality of sectors each comprising at least one vane which extends radially between an inner platform and an outer platform, the stator comprising at l...
|
|
WO/2020/065199A1 |
The invention relates to an assembly (2) for a turbomachine turbine comprising at least one ring sector (8) made of CMC material and a support casing (6) comprising an upstream flange (18) and a downstream flange (20) between which each ...
|
|
WO/2020/068114A1 |
A ring assembly in a gas turbine engine is provided. The ring seal assembly includes ring seal segments (50) supported by an interfit structure (52). Each ring seal segment is formed by a ceramic-based rhomboid body (54). A metal compres...
|
|
WO/2020/058612A1 |
The invention relates to a moving blade (1) for a wheel of an aircraft turbine engine, the blade (1) comprising an aerodynamic aerofoil (2) and an outer heel (7) defining said aerofoil (2). The heel (7) comprises a platform (8) and a fir...
|
|
WO/2020/058648A1 |
The invention relates to an assembly for a multistage turbine (10) of a turbomachine, the assembly comprising a static sealing device, a turbine stator (22) comprising a radially outer end and an outer casing (16) surrounding the stator ...
|
|
WO/2020/049243A1 |
The invention relates to a fan casing (200) for an aircraft turbomachine, such as a jet engine, said casing having a one-piece annular body (202), said body having a radially internal annular surface (206), a first annular portion (208) ...
|
|
WO/2020/049259A1 |
The invention relates to a pressurized-air supply unit (2) for an air-jet cooling device (1) cooling an outer casing (C) of a turbomachine turbine. This unit (2) is notable in that it is monobloc, in that it comprises: – a body (3) whi...
|
|
WO/2020/050835A1 |
A seal assembly (10) for sealing a circumferential gap (11) between a first machine component (38) and a second machine component (40) which is rotatable relative to the first machine component (38) about a longitudinal axis (42). The se...
|
|
WO/2020/050837A1 |
A seal assembly (86) for sealing a circumferential gap (11) between a first machine component (38) and a second machine component (40) which is rotatable relative to the first machine component (38) about a longitudinal axis (42). The se...
|
|
WO/2020/050834A1 |
A seal assembly (10) for sealing a circumferential gap (11) between a first machine component (38) and a second machine component (40) which is rotatable relative to the first machine component (38) about a longitudinal axis (42). The se...
|
|
WO/2020/049238A1 |
The invention relates to a rotor disc (36) for a turbomachine (10), the disc (36) extending circumferentially about an axis (A) and having a plurality of cells (60) configured to receive the roots of blades (58), each cell (60) having a ...
|
|
WO/2020/046375A1 |
A method for clearance control for at least one vane carrier (28, 50). The method includes having an inlet heating system (42) connected to an engine (10). The inlet heating system (42) extracts hot air from a component exit shell when a...
|
|
WO/2020/043541A1 |
The invention relates to a method for operating a gas turbine (100) comprising a rotor (103) with a plurality of rotor blades (120) and a housing (138), at least some of the rotor blades (120) being coated with a hard material, and an ab...
|
|
WO/2020/041445A1 |
A nested segmented assembly (100) and a method (300) of additively manufacturing the same are provided. In one example aspect, the assembly (100) includes a first component segment (110) and a second component segment (112) positioned ad...
|
|
WO/2020/039146A1 |
The invention relates to an abradable coating (2) comprising a matrix (21) and particles (22) dispersed in said matrix (21), the particles (22) being made of a material which changes to a fluid phase under the effect of the increase in t...
|
|
WO/2020/031625A1 |
The present invention of a rotary machine and a seal member comprises: a casing (11); a rotor (12) which is rotatably held in the casing (11); a stationary blade (13) which is fixed to the inner periphery of the casing (11); a moving bla...
|
|
WO/2020/025406A1 |
The invention relates to a rotor of a gas turbine, comprising two adjacent rotor disks (01, 06) having a plurality of blade-holding grooves (02) for receiving rotor blades, distributed around the periphery thereof, and comprising an axia...
|
|
WO/2020/021192A1 |
The invention relates to a turbine blade (13) for a turbomachine, comprising a turbine blade airfoil (14) extending radially, said turbine blade airfoil (14) having a leading edge (16) axially upstream and a trailing edge axially downstr...
|
|
WO/2020/021200A1 |
The invention relates to a stage of blades (16) with a longitudinal axis (X) intended to be mounted in a turbomachine compressor (10), comprising an annular row of movable blades (12) which are arranged upstream of an annular row of stat...
|
|
WO/2020/013109A1 |
A flow guide (27) is provided with a flange (41), a guide plate (42), an an inside member (43). A ring groove (44) which is recessed to the radially outer side from an inner circumferential surface (45) and which extends in a circumferen...
|
|
WO/2020/013950A1 |
A circumferential seal assembly (1 or 21) capable of dividing a gas into separate flow paths before communication between a rotatable runner (15, 35, or 67) and a pair of seal rings (3, 4 or 23, 24) is presented. The assembly (1 or 21) i...
|
|
WO/2020/014123A1 |
An intershaft seal assembly (2) for maintaining separation between a piston ring (3) and a pair of mating rings (4, 5) is presented. The assembly includes a piston ring (3) interposed between forward and aft mating rings (4, 5) and a plu...
|
|
WO/2020/013837A1 |
A sealing apparatus (30) for sealing a clearance between a stationary component (32) and a rotatable component (34) of a gas turbine engine includes a seal shoe (36) having oppositely facing first (38) and second (40) sides, the first si...
|
|
WO/2020/002357A1 |
The invention relates to a CMC moulding, such as for example a turbine component, of ceramic-matrix composite material "CMC", in particular also a ring segment of a gas turbine and/or a component of an exhaust system, which is at least p...
|
|
WO/2020/002799A1 |
The invention relates to a method for manufacturing an abradable layer (12), which comprises the following steps: - compressing a powder composition (30) comprising at least micrometric ceramic particles having a number average shape fac...
|
|
WO/2019/242854A1 |
The turbocharger for an internal combustion engine comprises a compressor (1) for pressurizing intake air, the compressor (1) comprising a compressor wheel (3), a turbine (2) for driving the compressor (1), the turbine (2) comprising a t...
|
|
WO/2019/246369A1 |
The present disclosure relates to techniques for extracting heat energy from geothermal briny fluid. A briny fluid can be extracted from a geothermal production well and delivered to a heat exchanger. The heat exchanger can receive the b...
|
|
WO/2019/243708A2 |
The invention relates to a labyrinth sealing joint (100) for a turbomachine, in particular of an aircraft, comprising a rotor element (114) extending about an axis (A), and a stator element (116) extending around the rotor element (114),...
|
|
WO/2019/239064A1 |
The invention relates to a turbine nozzle (22) for an aircraft turbine engine, said nozzle comprising at least one vane (28) and a base (32) having a platform (30). The nozzle (22) is fitted with a passive system (56) for reintroducing b...
|
|
WO/2019/229322A1 |
The invention relates to a sealing arrangement between two ring-shaped walls (9, 10) of an aircraft engine, namely a radially inner wall (9) and a radially outer wall (10) respectively, said two walls being coaxially engaged one inside t...
|
|
WO/2019/231786A1 |
A turbine that includes an inner shroud segment (35) having a cooling configuration in which interior channels (60) are configured to receive and direct a coolant. The cooling configuration may include a pair of counterflowing crossflow ...
|
|
WO/2019/229377A1 |
The invention relates to a device (21) for cooling an annular housing (18) of a turbomachine, comprising a collector box (22) designed to extend circumferentially around the axis of the housing (18), at least two cooling tubes (23) exten...
|
|
WO/2019/231750A1 |
A turbine having a stationary shroud ring (34) formed about rotor blades (33). The stationary shroud ring may include an inner shroud segment (35). The inner shroud segment may include a cooling configuration that includes a crossflow ch...
|
|
WO/2019/231838A1 |
A turbine of a gas turbine engine that includes a stationary shroud ring having inner shroud segments (35) circumferentially stacked about a hot gas path (38). The inner shroud segments may include a first inner shroud segment (35a) that...
|
