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公开(公告)号：US20240360773A1
公开(公告)日：2024-10-31
申请号：US18643156
申请日：2024-04-23
发明人： Magdalena Angelika LULA , Thomas Alan MOGLE, II , Christopher David RUNKEL , Sandra Beverly KOLVICK , Nicholas Desmond DUPRE , Kelly Anne MCMANUS
IPC分类号： F01D25/24
CPC分类号： F01D25/24 , F05D2230/60 , F05D2300/601
摘要： A foreign material exclusion system for positioning within a casing of a turbine to catch any foreign material during maintenance of the turbine. The foreign material exclusion system may include a fabric sleeve with a semicircular shape and a number of poles attached to the sleeve to maintain the sleeve in place within the turbine casing.
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公开(公告)号：US12129763B2
公开(公告)日：2024-10-29
申请号：US18274645
申请日：2022-02-02
CPC分类号： F01D17/162 , F01D25/24 , F04D19/02 , F04D29/52 , F04D29/54 , F04D29/56 , F04D29/563 , F04D29/64 , F05D2220/323 , F05D2240/128 , F05D2260/60
摘要： An inner ring for supporting variable-pitch blades of an axial compressor stator of a turbomachine includes two or more ring sectors, assembled to form the inner ring, each ring sector including plural housings for receiving a pivot axis of one of the blades. At each junction plane between the ends of two successive ring sectors, an assembly pin and a cavity for receiving the assembly pin are engaged. The assembly pin is fixed on one end one of the two successive ring sectors and the cavity is formed at the end of the other of the two successive ring sectors. The cavity receives the assembly pin with a mounting clearance allowing a mounting by sliding fit, and the assembly pin is made of a material having a coefficient of thermal expansion greater than a coefficient of thermal expansion of a material constituting the successive ring sectors.
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公开(公告)号：US12116902B2
公开(公告)日：2024-10-15
申请号：US17692534
申请日：2022-03-11
发明人： Tomas Hebnar , Jakub Vymyslicky , Michal Planka
摘要： A turbine assembly can include a turbine housing that defines a longitudinal axis and that includes a first scroll and a first tongue at a first angle about the longitudinal axis and a second scroll and a second tongue at a second angle about the longitudinal axis, where an angular span between the first angle and the second angle is greater than 1 degree and less than 180 degrees; and a first set of vanes and a second set of vanes disposed in the turbine housing, where a vane of the first set of vanes is aligned with the first tongue and a vane of the second set of vanes is aligned with the second tongue.
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公开(公告)号：US12110120B2
公开(公告)日：2024-10-08
申请号：US18255025
申请日：2021-12-01
申请人： SAFRAN NACELLES
CPC分类号： B64D27/40 , B64D29/06 , B64D29/08 , F01D25/243 , F01D25/28 , F02C7/00 , F02C7/04 , F02C7/20 , F05D2220/323
摘要： A propulsion unit for an aircraft includes a gas generator; an air inlet; and a sealing system inserted axially between the air inlet and the gas generator. The sealing system has at least: a compression ring with a first axial end configured for mechanical connection to one of the gas generator and the air inlet. The compression ring also has a second opposite axial end configured to be axially separated from the other of the gas generator and the air inlet by an annular space. An annular seal is mounted in the space and configured to be axially compressed by reduction of the axial dimension of said space.
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公开(公告)号：US12109618B2
公开(公告)日：2024-10-08
申请号：US17197266
申请日：2021-03-10
IPC分类号： B32B15/01 , B22F3/15 , B22F3/24 , B22F5/00 , B22F5/04 , B22F10/14 , B22F10/28 , B22F10/62 , B22F10/64 , B23K15/00 , B23K26/00 , B23K26/342 , B23K26/70 , B32B3/30 , B33Y10/00 , B33Y40/20 , B33Y70/00 , B33Y80/00 , C22C19/05 , C22C19/07 , C22C30/02 , C22C38/00 , C22C38/02 , C22C38/04 , C22C38/06 , C22C38/08 , C22C38/10 , C22C38/42 , C22C38/44 , C22C38/48 , C22C38/50 , C22C38/52 , C23C4/08 , C23C4/134 , C23C14/16 , C23C14/28 , C23C16/06 , C23C16/44 , C23C18/16 , C23C18/32 , F01D5/28 , F01D25/00 , F01D25/24 , B23K101/00
CPC分类号： B22F3/15 , B22F3/24 , B22F5/009 , B22F5/04 , B22F10/14 , B22F10/28 , B22F10/62 , B22F10/64 , B23K15/0086 , B23K15/0093 , B23K26/0006 , B23K26/342 , B23K26/70 , B32B3/30 , B32B15/01 , B33Y10/00 , B33Y40/20 , B33Y70/00 , B33Y80/00 , C22C19/055 , C22C19/056 , C22C19/057 , C22C19/07 , C22C30/02 , C22C38/002 , C22C38/02 , C22C38/04 , C22C38/06 , C22C38/08 , C22C38/105 , C22C38/42 , C22C38/44 , C22C38/48 , C22C38/50 , C22C38/52 , C23C4/08 , C23C4/134 , C23C14/16 , C23C14/28 , C23C16/06 , C23C16/44 , C23C18/1637 , C23C18/32 , F01D5/28 , F01D25/005 , F01D25/24 , B22F2003/242 , B22F2301/15 , B22F2301/35 , B22F2998/10 , B23K2101/001 , F05D2300/17 , Y02P10/25 , B22F2998/10 , B22F10/28 , B22F10/62 , B22F2003/242 , B22F10/64 , B22F3/15
摘要： A process includes forming a printed article having an external surface and at least one microfeature with an internal surface by additive manufacture, coating the external surface and the internal surface of the printed article with a metallic microlayer to form a coated article, and densifying the coated article to form a component. After formation, the printed article has a porosity such that the printed article is not at full density. A densified component includes a printed article having an external surface and at least one microfeature with an internal surface and a metallic microlayer coating the external surface and the internal surface of the printed article. The printed article is formed by additive manufacture.
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公开(公告)号：US12104497B2
公开(公告)日：2024-10-01
申请号：US18250898
申请日：2021-10-27
申请人： SAFRAN CERAMICS
CPC分类号： F01D25/005 , F01D9/04 , F01D11/005 , F01D25/246 , F05D2300/20 , F05D2300/6033
摘要： An assembly for a turbine includes a plurality of sectors which are adjacent to one another, each sector including at least one connecting edge of composite material with a ceramic matrix, each connecting edge including at least one groove and a sealing tongue present in each groove. Each sealing tongue has a laminated structure comprising a plurality of strips the lower strip and the upper strip of the laminated structure, each being formed by a film of monolithic ceramic material.
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公开(公告)号：US20240318581A1
公开(公告)日：2024-09-26
申请号：US18610034
申请日：2024-03-19
申请人： Cummins Ltd
发明人： Christopher Gentle , David Michael Eastwood , Jonathan Dickson , Pravin Nirgude , Sarendra S. Gehlot , Kalpeshbapu Sonar
IPC分类号： F01D25/24
CPC分类号： F01D25/243 , F05D2250/75
摘要： There is disclosed a turbine housing for a turbomachine. The turbine housing comprises a volute which extends around an axis and defines at least part of a flow passage through the turbine housing. The flow passage extends from a first inlet opening. The turbine housing further comprises a flange that surrounds the first inlet opening, and an external surface that defines a rib. The rib defines a first portion that adjoins the flange, and a second portion that is angled with respect to the first portion.
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公开(公告)号：US12098648B2
公开(公告)日：2024-09-24
申请号：US18249230
申请日：2021-10-13
IPC分类号： F01D25/24
CPC分类号： F01D25/243 , F05D2260/31
摘要： An aircraft turbomachine module having two tubular casings equipped with first and second annular flanges assembled by studs received in the first flange and receiving nuts on the back of the second flange, each stud having an intermediate stretch of hexagonal shape cooperating with a locking plate. The locking plate can have a first orifice received on the intermediate stretch by at least two opposite walls, and a transverse body which is immobilized to prevent the rotation of the plate and that of the stud. Each plate can be fitted on two immediately adjacent studs and the body can have, for this purpose, a second orifice opposite the first orifice and which is received on an intermediate stretch of an immediately adjacent stud and cooperates with the intermediate stretch of hexagonal shape of the stud.
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公开(公告)号：US20240309779A1
公开(公告)日：2024-09-19
申请号：US18183612
申请日：2023-03-14
发明人： Bernard W. Pudvah
CPC分类号： F01D25/14 , B23P15/00 , F01D9/041 , F01D25/12 , F01D25/24 , F05D2230/21 , F05D2260/20
摘要： Manufacturing a compressor case by casting a member having: forward and aft annular portions; a cavity forward wall extending from the forward annular portion to a first inner end; a cavity aft wall extending from the aft annular portion to a second inner end; a cavity outer wall extending between the forward and aft annular portions and defining an outer aperture; casting a cavity inner wall and welding the cavity inner wall between the cavity forward and aft walls such that the cavity inner wall is offset from the first and second inner ends of the cavity forward and aft walls to form a U-shaped end channel, the compressor case is capable of receiving a vane so that a trunnion bearing extends from a vane root to a trunnion bearing outer end, through the inner aperture in the cavity inner wall and the outer aperture in the cavity outer wall.
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公开(公告)号：US12091983B2
公开(公告)日：2024-09-17
申请号：US18020110
申请日：2021-07-26
发明人： Kenichi Sakashita , Shouhei Danno
CPC分类号： F01D25/32 , F01D9/02 , F01D11/001 , F01D25/24 , F05D2220/31
摘要： A stator blade segment includes a circumferentially extending outer blade ring, a stator blade extending radially inward from the outer blade ring, and a sealing member. The stator blade has a cavity that is formed in the interior of the blade and that communicates with the surface of the blade. The outer blade ring has a blade ring body and two blade ring protrusions. The two blade ring protrusions protrude radially outward from an anti-gas path surface of the blade ring body and face each other across a gap in an axial direction, and together with a casing, a drain recovery space is formed between the two blade ring protrusions. The blade ring body has a blade surface drain recovery passage that allows communication between the cavity and the drain recovery space. One of the two blade ring protrusions has a sealing surface.
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