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公开(公告)号：US20240011453A1
公开(公告)日：2024-01-11
申请号：US18035574
申请日：2021-11-03
申请人： SAFRAN NACELLES
摘要： The invention relates to an assembly for a turbine of a turbomachine with a longitudinal axis (X) comprising:
an exhaust cone (100) comprising an outer annular wall (102) for the flow of a primary airflow and an annular box arranged radially inside said outer annular wall (102), the annular box comprising an inner annular wall (104) arranged radially inside the outer annular wall of the exhaust cone,
an exhaust case arranged upstream of the exhaust cone, and
a connecting member (106) flexible in a radial direction, interposed longitudinally between the exhaust case and the exhaust cone (100), the connecting member being fastened to the exhaust case and to the inner annular wall (104), and
wherein the inner annular wall (104) is connected to the outer annular wall (102) by fastening means (112) configured to enable movements of the inner annular wall (104) in a circumferential direction and a longitudinal direction with respect to the outer annular wall (102).
Figure to be published with the abstract: FIG. 2-
公开(公告)号：US20230407814A1
公开(公告)日：2023-12-21
申请号：US18251965
申请日：2021-11-04
申请人： SAFRAN CERAMICS
发明人： Thomas VANDELLOS , Benoit CARRERE , Eric CONETE , Jean-Philippe JORET , Vincent DEVANLAY , Clément Marie Benoît ROUSSILLE
摘要： An assembly for a turbomachine with a longitudinal axis having an exhaust cone with an outer annular wall for the flow of a primary airflow and an annular box arranged radially inside the outer annular wall, an exhaust casing arranged upstream of and connected to the exhaust cone. One end of the outer annular wall or one end of the annular box may be free to move relative to and have no mechanical connection with the exhaust cone or the exhaust casing.
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公开(公告)号：US11319895B2
公开(公告)日：2022-05-03
申请号：US16354357
申请日：2019-03-15
发明人： Todd A. Spierling
摘要： A gas turbine engine including: a tail cone; a low pressure compressor; a low pressure turbine; a low speed spool interconnecting the low pressure compressor and the low pressure turbine; an electric generator located within the tail cone, the electric generator being operably connected to the low speed spool; a structural support housing at least partially enclosing the electric generator, the structural support housing being located within the tail cone; and a mounting system located within the tail cone between the structural support housing and the tail cone, wherein the mounting system attaches the tail cone to the structural support housing.
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公开(公告)号：US11136942B2
公开(公告)日：2021-10-05
申请号：US16131420
申请日：2018-09-14
申请人： Rohr, Inc.
发明人： Carlos A. Lopez , Lisa K. Martini-Saliers , David Gaul , Jose S. Alonso-Miralles , Keith E. Ritchie
摘要： Aspects of the disclosure are directed to a sound-absorbing exhaust center plug for an aircraft gas turbine engine comprising a center plug adapted for attachment within an exhaust nozzle of the engine. The center plug comprises an outer skin, and at least one cavity within the center plug and the at least one cavity extending between a forward bulkhead and an aft bulkhead, where the aft bulkhead is canted inwardly. The outer skin includes a plurality of outer skin openings providing an acoustic pathway through the outer skin and into the at least one cavity.
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公开(公告)号：US20210293201A1
公开(公告)日：2021-09-23
申请号：US17267361
申请日：2019-08-09
申请人： SAFRAN CERAMICS
发明人： Eric Conete , Benoit Carrere
摘要： An assembly for an aircraft turbojet engine is described. The assembly includes a central gas-exhaust element and a connecting flange interposed between, upstream, a metallic outlet of a turbojet engine and, downstream, the central element. The connecting flange consists of an annular part and flexible lugs having axially: a first end where the lug is connected to the annular part, and a second free end, projecting radially outwards from the first end and towards which the lug is fixed with the central element.
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公开(公告)号：US11118481B2
公开(公告)日：2021-09-14
申请号：US15424930
申请日：2017-02-06
发明人： Gabriel L. Suciu , Brian Merry , Ioannis Alvanos
摘要： A turbine exhaust assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, a turbine exhaust case comprised of CMC material and attachable to a turbine case, a tail cone comprised of CMC material that has a leading edge and a trailing edge, and an exhaust mixer comprised of CMC material and coupled to the turbine exhaust case. The exhaust mixer has a plurality of lobes arranged about the tail cone to define an exhaust flow path. A plurality of struts extend from the tail cone to support the exhaust mixer at a location aft of the leading edge of the tail cone. A method of assembling a propulsion system is also disclosed.
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公开(公告)号：US20200291890A1
公开(公告)日：2020-09-17
申请号：US16354357
申请日：2019-03-15
发明人： Todd A. Spierling
摘要： A gas turbine engine including: a tail cone; a low pressure compressor; a low pressure turbine; a low speed spool interconnecting the low pressure compressor and the low pressure turbine; an electric generator located within the tail cone, the electric generator being operably connected to the low speed spool; a structural support housing at least partially enclosing the electric generator, the structural support housing being located within the tail cone; and a mounting system located within the tail cone between the structural support housing and the tail cone, wherein the mounting system attaches the tail cone to the structural support housing.
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公开(公告)号：US10724131B2
公开(公告)日：2020-07-28
申请号：US15096685
申请日：2016-04-12
发明人： Gary D. Roberge
IPC分类号： B22F7/00 , B22F3/11 , C22C1/08 , B32B5/18 , C23C4/129 , F02C7/12 , B32B15/01 , F02K1/78 , B32B5/20 , F02K1/04 , B23K26/40 , B23K26/361 , C23C4/134 , C23C14/22 , C23C16/06 , C23C24/04 , B23K103/02 , B23K103/08
摘要： A method of making a light weight component is provided. The method including the steps of: forming a metallic foam core into a desired configuration; and applying an external metallic shell to an exterior surface of the metallic foam core after it has been formed into the desired configuration.
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公开(公告)号：US10527000B2
公开(公告)日：2020-01-07
申请号：US15364550
申请日：2016-11-30
发明人： Christian Wellhausen
摘要： An aircraft with at least one engine that generates a hot air flow in operation of the aircraft, wherein at least one hot air exhaust is provided for exhausting the generated hot air flow, the at least one hot air exhaust comprising at least one first exhaust section that is mounted in a rotatable manner to at least one second exhaust section via an associated off-axis swivel joint, wherein an actuating member is provided that is adapted for applying a turning moment to the at least one second exhaust section in operation of the aircraft in order to displace a longitudinal axis of the at least one second exhaust section with respect to a longitudinal axis of the at least one first exhaust section by a predetermined displacement angle.
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公开(公告)号：US20190284959A1
公开(公告)日：2019-09-19
申请号：US16395798
申请日：2019-04-26
IPC分类号： F01D25/26 , B32B3/26 , B32B5/26 , C04B35/80 , F01D25/00 , B32B3/06 , F01D25/28 , F02K1/04 , F02K1/80 , F01D25/24
摘要： The present disclosure is directed to a composite component defining a component aperture extending between a first surface and a second surface. The composite component includes an insert having an insert annular wall positioned in the component aperture. The insert annular wall defines an insert aperture therethrough. An insert flange extends radially outwardly from the insert annular wall and contacts the first surface of the composite component. The insert flange includes a diameter about 1.5 times to about 5 times greater than a smallest diameter of the component aperture defined by the composite component.
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