公开(公告)号：US11753957B2

公开(公告)日：2023-09-12

申请号：US17602967

申请日：2020-04-10

申请人： SAFRAN AIRCRAFT ENGINES

发明人： Clément Bourolleau ,  Alexandre Branco ,  Serge Domingues ,  Vincent Fiore ,  Anwer Siraj

IPC分类号： F01D11/12 ,  F01D21/00 ,  F01D25/24

CPC分类号： F01D11/122 ,  F01D21/003 ,  F01D25/24 ,  F05D2230/31 ,  F05D2300/516 ,  F05D2300/6111

摘要： A method for detecting at least one roughness in a face of an abradable layer in a fan casing is provided. The method includes a step of depositing on the abradable layer a first coating and a second coating covering the first coating. The first and second coatings have respective thicknesses (N1, N2) and a physical appearance that differ from one another. Local appearance of the first coating is indicative of a need for a localized touch-up, and local disappearance of the first coating and the second coating is indicative of a need for a localized replacement of the abradable layer.

公开(公告)号：US11746668B2

公开(公告)日：2023-09-05

申请号：US17913917

申请日：2021-03-22

申请人： Safran Aircraft Engines

发明人： Clément Jarrossay ,  Clément Emile André Cazin ,  Sébastien Serge Francis Congratel ,  Antoine Claude Michel Etienne Danis ,  Aurélien Gaillard

IPC分类号： F01D11/08 ,  F01D11/00 ,  F01D25/24

CPC分类号： F01D11/005 ,  F01D25/246 ,  F05D2260/201

摘要： The invention relates to a turbine assembly comprising: a plurality of ring sectors forming a ring; a support structure comprising a shroud from which there project radial flanges which serve to hold latching tabs of each ring sector; a stator positioned downstream of said ring and comprising a blade provided with a radially outer platform and extending axially opposite said ring; an annular space being defined between the ring, the support structure and the platform, this annular space having passing through it a leakage air current, the assembly comprising a hollow ring which occupies said annular space and which is shaped so as to collect, channel and expel said leakage air current, more specifically to channel and expel it into the radially inner region of said annular space.

公开(公告)号：US20230265769A1

公开(公告)日：2023-08-24

申请号：US18308806

申请日：2023-04-28

申请人： General Electric Company

发明人： Jason David Shapiro ,  Jan Christopher Schilling ,  Michael John Franks

IPC分类号： F01D25/24 ,  F01D25/12

CPC分类号： F01D25/246 ,  F01D25/24 ,  F01D25/12 ,  Y02T50/60 ,  F05D2220/32 ,  F05D2250/131 ,  F05D2300/50212

摘要： A shroud hanger assembly (30) or shroud assembly is provided for dimensionally incompatible components wherein the assembly includes a multi-piece hanger (32), for example having a forward hanger portion (34) and a rearward hanger portion (36). A cavity (46) is formed between the parts; wherein a shroud (50) may be positioned which is formed of a low coefficient of thermal expansion material. The hanger (32) and shroud (50) may be formed of the same material or differing materials in order to better match the thermal growth between the hanger and the shroud. When the shroud (50) is positioned within the hanger opening or cavity (46), one of the forward (34) and rearward hanger (36) portions may be press fit or otherwise connected into the other of the forward (34) and rearward (36) hanger portion.

公开(公告)号：US11732598B2

公开(公告)日：2023-08-22

申请号：US17554819

申请日：2021-12-17

申请人： Rolls-Royce Corporation ,  Rolls-Royce High Temperature Composites Inc.

发明人： Ted J. Freeman ,  Jeremy Roehm

IPC分类号： F01D11/12 ,  F01D25/00 ,  F01D25/28 ,  F01D25/24

CPC分类号： F01D11/122 ,  F01D25/005 ,  F01D25/24 ,  F01D25/28 ,  F05D2240/11 ,  F05D2250/75 ,  F05D2260/30 ,  F05D2300/6033 ,  F05D2300/6111

摘要： A turbine shroud segment for use in a gas turbine engine includes a ceramic shroud segment formed to define a circumferentially extending channel that opens radially inwardly and a layer of abradable material that extends axially along a radial inner surface of the ceramic shroud segment to provide a flow path surface of the turbine shroud segment.

公开(公告)号：US11719164B2

公开(公告)日：2023-08-08

申请号：US16212010

申请日：2018-12-06

申请人： United Technologies Corporation

发明人： Gary D. Roberge

IPC分类号： F02C7/32 ,  F01D25/24 ,  F01D25/16 ,  B33Y80/00

CPC分类号： F02C7/32 ,  F01D25/162 ,  F01D25/24 ,  B33Y80/00 ,  F05D2220/323

摘要： A gas turbine engine includes an engine case along an engine axis, a conformal accessory drive gearbox housing mounted to the engine case, and at least one accessory mounted to the conformal housing.

公开(公告)号：US20230243274A1

公开(公告)日：2023-08-03

申请号：US17587883

申请日：2022-01-28

申请人： Hamilton Sundstrand Corporation

发明人： Viktor Kilchyk ,  Christopher Simpson

IPC分类号： F01D21/04 ,  F01D25/24 ,  F01D25/00

CPC分类号： F01D21/045 ,  F01D25/243 ,  F01D25/005 ,  F05D2220/34 ,  F05D2240/14 ,  F05D2300/603 ,  F05D2250/18

摘要： A containment structure for a rotor includes a shroud and a shroud reinforcement. The shroud is coaxial with and partially surrounds the rotor and includes a tubular section, a transition section, and a flange section. The tubular section extends axially past a first side of the rotor. The transition section connects to the tubular section and is adjacent to a curved side of the rotor. The flange section connects to the transition section opposite the tubular section. The flange section extends radially past a radially outer side of the rotor. The shroud reinforcement is connected to a radially outer surface of the transition section. The shroud reinforcement encloses the transition section and includes a support scaffold and a reinforcing material. The support scaffold includes a series of geometric retaining features encircling a radially outer surface of the transition section. The reinforcing material couples to the support scaffold and restricts shroud radial expansion.

公开(公告)号：US11713694B1

公开(公告)日：2023-08-01

申请号：US18072145

申请日：2022-11-30

申请人： Rolls-Royce Corporation

发明人： Ted J. Freeman ,  Aaron D. Sippel

IPC分类号： F01D25/24 ,  F01D11/08 ,  F01D25/00

CPC分类号： F01D25/243 ,  F01D11/08 ,  F01D25/005 ,  F01D25/246 ,  F05D2230/60 ,  F05D2260/30 ,  F05D2300/6033

摘要： A turbine shroud assembly includes a carrier assembly, a blade track segment, and a retainer. The carrier assembly is arranged circumferentially at least partway around an axis and includes a fore carrier segment and an aft carrier segment coupled with the fore carrier. The blade track segment is supported by the carrier assembly to locate the blade track segment radially outward of the axis and define a portion of a gas path of the turbine shroud assembly. The retainer extends into the fore carrier segment, the blade track segment, and the aft carrier segment to couple the blade track segment with the carrier assembly.

公开(公告)号：US20230235682A1

公开(公告)日：2023-07-27

申请号：US18157392

申请日：2023-01-20

申请人： ROLLS-ROYCE plc

发明人： Mark BECKHAM ,  Richard HALL

IPC分类号： F01D25/00 ,  F01D25/24

CPC分类号： F01D25/005 ,  F01D25/24 ,  F05D2220/323 ,  F05D2240/14 ,  F05D2300/6031

摘要： A fan casing for an engine having a fan with fan blades that each have a centre of gravity (CoG) that lies on a fan blade CoG plane, the fan casing having a central axis and comprising a main impact region comprising carbon-fibre reinforced polymer (CFRP) blocks and glass-fibre reinforced polymer (GFRP) blocks having a constant thickness throughout the axial extent of the main impact region, wherein the total depth of the main impact region is equal to the sum of the thicknesses of the CFRP blocks and GFRP blocks, each of the GFRP blocks is positioned between two CFRP blocks, and the thickness of at least one of the GFRP blocks is different to the thickness of another of the GFRP blocks.

公开(公告)号：US11692454B2

公开(公告)日：2023-07-04

申请号：US17453501

申请日：2021-11-04

申请人： ROLLS-ROYCE plc

发明人： Benjamin Mohankumar ,  Mark J. Wilson ,  Cesare A. Hall

IPC分类号： F01D15/12 ,  F02C7/04 ,  F01D25/24 ,  F02K3/068

CPC分类号： F01D15/12 ,  F01D25/24 ,  F02C7/04 ,  F02K3/068 ,  F05D2220/32 ,  F05D2260/4031

摘要： An aircraft engine comprising a fan, the fan having a diameter D and including a plurality of fan blades, the fan blades having a sweep metric Stip, each fan blade having a leading edge, and a forward-most portion on the leading edge of each fan blade being in a first reference plane. The aircraft engine further comprises a nacelle, comprising an intake portion forward of the fan, a forward edge on the intake portion being in a second reference plane, wherein the intake portion has a length L measured along an axis of the aircraft engine between the first reference plane and the second reference plane, the aircraft engine having a cruise design point condition Mrel, wherein Mrel is between 0.4 and 0.93, L/D is between 0.2 and 0.45 and Stip is from −1 to 0.1.

公开(公告)号：US11686221B2

公开(公告)日：2023-06-27

申请号：US17539785

申请日：2021-12-01

申请人： PRATT & WHITNEY CANADA CORP.

发明人： Carlo Porco ,  Geoffrey Henriksen ,  Jason Wedemire ,  Anthony Mathias ,  Michael Hunze ,  Louis Lavoie ,  Marven Paynter ,  Dennis Wilkinson

IPC分类号： F01D25/28 ,  F01D25/24

CPC分类号： F01D25/285 ,  F01D25/24 ,  F05D2220/323 ,  F05D2230/72 ,  F05D2230/80

摘要： An aircraft engine repair tool for installing and/or removing a mid turbine frame from a gas turbine engine is provided. The tool includes a stabilizer configured to support a shaft via a load path different from a load path provided by the mid turbine frame rotatably supporting the shaft about a rotation axis. The tool includes a holder attachable to the mid turbine frame, and a guide movably engageable with the shaft and attachable to the holder. The guide guides movement of the holder and of the mid turbine frame relative to the shaft along the rotation axis, and prevents movement of the holder and the mid turbine frame relative to the shaft transverse to the rotation axis when the mid turbine frame is released from the support structure and attached to the holder, and when the holder is attached to the guide.