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公开(公告)号：US11624441B2
公开(公告)日：2023-04-11
申请号：US17245715
申请日：2021-04-30
发明人： Robert A. White, III
IPC分类号： F16J15/3288 , F01D11/00
摘要： A seal assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, a first side plate and a backing plate that extend circumferentially about an assembly axis. The backing plate includes a main body and a first set of abutments that extend outwardly from the main body to abut the first side plate. A first set of pockets are established between adjacent abutments of the first set of abutments. A first brush seal is between the first side plate and the backing plate. Sections of the first brush seal received in respective pockets of the first set of pockets are dimensioned to join together to establish a first sealing relationship with a first gas turbine engine component. A method of assembly is also disclosed.
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2.发明申请公开(公告)号：US20230099406A1
公开(公告)日：2023-03-30
申请号：US17817159
申请日：2022-08-03
申请人： MTU Aero Engines AG
发明人： Werner Humhauser
摘要： The invention relates to a guide vane ring for a turbomachine comprising at least one guide vane, at least one bearing body, and at least two inner ring segments. The guide vane has a bearing journal that is arranged in a in form-fitting manner in a bearing bush of the at least one bearing body. The at least two inner ring segments have on their respective outer radial faces a guide channel running along a circumferential direction of the guide vane ring for receiving the bearing body, into which project at least two opposite-lying guide projections of the inner ring segments, said projections running along the circumferential direction of the guide vane ring. The bearing bodyis arranged in the guide channel of the inner ring segments, and the at least two guide projections of the inner ring segments engage in at least two guide grooves of the bearing body.
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公开(公告)号：US20230087593A1
公开(公告)日：2023-03-23
申请号：US17802062
申请日：2021-02-19
申请人： SAFRAN CERAMICS
摘要： Assembly in a turbine comprising: —at least one turbine ring made of a ceramic composite having a silicon carbide SiC matrix and fibers, the ring comprising a plurality of sectors (10) arranged circumferentially end to end, each of the ring sectors (10) comprises at least one circumferential edge (26, 28) provided with at least one slot (30a, 30b, 30c) opening circumferentially, —at least one sealing member being inserted for a first part into one of the slots (30a, 30b, 30c) of an edge of a first ring sector and for a second part into one of the slots (30a, 30b, 30c) of an edge of a second ring sector, circumferentially adjacent to the first ring sector, the assembly being characterized in that the sealing member is made of a ceramic matrix composite.
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公开(公告)号：US11608747B2
公开(公告)日：2023-03-21
申请号：US17143855
申请日：2021-01-07
发明人： Ravindra Shankar Ganiger , Sam J. Stoughton , Kevin Lee Kirkeng , Jacob P. Miller , Reddi Hari Prasad Reddy Mylapalli , Paul Trimby , Jaeyong Kim
IPC分类号： F01D5/22 , F02C7/28 , F01D25/04 , F01D5/16 , F01D25/06 , F01D5/26 , F01D17/16 , F04D29/66 , F01D11/00 , F04D29/56
摘要： Methods, apparatus, systems and articles of manufacture are disclosed. A split shroud for an inner shroud of a gas turbine engine includes: at least one forward shroud segment and at least one aft shroud segment to couple to the at least one forward shroud segment, the at least one forward shroud segment and the at least one aft shroud segment forming a split line.
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公开(公告)号：US11597991B2
公开(公告)日：2023-03-07
申请号：US15633114
申请日：2017-06-26
摘要： An abrasive coating for a substrate including a metallic based bond coat layer; a top layer; and an intermediate layer between the metallic based bond coat layer and the top layer. A method of applying an abrasive coating including applying a metallic based bond coat layer onto a substrate; grading an intermediate layer into the metallic based bond coat layer to form a graded transition between the metallic based bond coat layer and the intermediate layer; and grading a top layer into the intermediate layer to form a graded transition between the intermediate layer and the top layer.
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公开(公告)号：US11560811B2
公开(公告)日：2023-01-24
申请号：US16805309
申请日：2020-02-28
发明人： Anthony R. Bifulco
摘要： A system for retaining stators and reducing air leakage in a gas turbine engine having an axis includes a stator having an inner platform, an outer platform, a low pressure side, a high pressure side, and at least one foot, and designed to turn air. The system also includes a case positioned radially outward from the stator and having at least one recess designed to interface with the at least one foot to resist movement of the stator relative to the case. The system also includes a bladder positioned between the outer platform of the stator and the case and designed to receive pressurized fluid having a greater pressure than ambient pressures experienced at the low pressure side of the stator and to further resist movement of the stator relative to the case in response to receiving the pressurized fluid.
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公开(公告)号：US11549385B2
公开(公告)日：2023-01-10
申请号：US17307074
申请日：2021-05-04
摘要： An airfoil assembly includes an airfoil fairing, a spar, a seal plate, and a seal. The airfoil fairing has a fairing platform and a hollow airfoil section that extends from the fairing platform. The spar has a spar leg that extends in the hollow airfoil section. The spar leg defines a spar leg periphery. The seal plate is secured with the fairing platform. The seal plate has an opening, and the opening has an opening periphery that is complementary to the spar leg periphery. The spar leg extends through the opening. The seal is between the seal plate and the spar leg. The seal seals around the spar leg periphery.
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8.发明授权公开(公告)号：US11542825B2
公开(公告)日：2023-01-03
申请号：US17520756
申请日：2021-11-08
发明人： Simon Hauswirth , Wade Beaumont , Vincent Galoul , Richard Jones , Yunchang Jang
摘要： The present invention presents a ring assembly 1 disposed radially outwardly of an array of circumferentially arranged blades 38 of a gas turbine engine rotor R. The ring assembly 1 includes ring segments 2 disposed circumferentially one adjacent to another and having a first circumferential end 2a and a second circumferential end 2b circumferentially spaced apart from each other. The first end 2a of a ring segment 2 and the second end 2b of an adjacent ring segment 2 of the plurality of ring segments 2 are arranged facing each other. An integrally formed projecting seal part 92 is formed at the first end 2a. An integrally formed receiving seal part 94 is formed at the second end 2b facing the first end 2a. The receiving seal part 94 receives the projecting seal part 92 to form a mating connection between the ring segment 2 and the adjacent ring segment 2. A gas turbine engine including the ring assembly 1 is also provided. Furthermore, a method of manufacturing the ring segment 2 of the ring assembly 1 is also provided.
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公开(公告)号：US20220412462A1
公开(公告)日：2022-12-29
申请号：US17304762
申请日：2021-06-25
发明人： Aaron G. Glafenhein
IPC分类号： F16J15/324 , F01D11/00
摘要： A noncontacting intershaft seal system includes force generating mechanisms to reduce contact related effects. A sealing system includes an outer shaft that has a hollow interior. An inner shaft extends through the hollow interior of the outer shaft. Spaced apart end plates encircle and rotate with the inner shaft. A gland opening is defined between the inner and outer shafts and between the end plates. A ring is disposed in the gland opening. The end plates and/or the ring include force generating elements that generate force to separate the ring from the end plates, reducing contact related heat generation and wear.
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公开(公告)号：US20220411334A1
公开(公告)日：2022-12-29
申请号：US17861722
申请日：2022-07-11
发明人： David C. Jarmon
IPC分类号： C04B35/01 , B28B23/00 , B29C70/02 , F02C7/20 , F01D5/00 , F01D25/24 , F01D25/00 , C04B37/00 , C04B35/571 , F23R3/00 , C04B35/565 , F23R3/60 , F01D9/00 , F01D25/30 , C04B35/83 , F23R3/28 , F01D11/00 , F02K1/82 , C04B35/80
摘要： A method of forming an integral fastener for a ceramic matrix composite component comprises the steps of forming a fiber preform with an opening, forming a fiber fastener, inserting the fiber fastener into the opening, and infiltrating a matrix material into the fiber preform and fiber fastener to form a ceramic matrix composite component with an integral fastener. A gas turbine engine is also disclosed.
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