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公开(公告)号：US12140107B2
公开(公告)日：2024-11-12
申请号：US18556312
申请日：2022-04-27
Applicant: SAFRAN NACELLES
Inventor： Sebastien Laurent Marie Pascal , Luigi Bisanti
Abstract: A thrust reverser for an aircraft bypass turbojet engine nacelle, this thrust reverser having a generally annular shape around an axis and including in particular flaps for deflecting the secondary flow through gratings, each of these flaps having a rigid wall and sealing elements located on the outer face of this wall, these sealing elements extending along side edges of the flap so as to provide a seal along these edges in the first position.
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公开(公告)号：US12116954B2
公开(公告)日：2024-10-15
申请号：US18035574
申请日：2021-11-03
Applicant: SAFRAN NACELLES
Inventor： Jean-Philippe Joret , Vincent Devanlay , Fabien Bravin , Boualem Merabet
Abstract: 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).-
公开(公告)号：US20240287950A1
公开(公告)日：2024-08-29
申请号：US18657373
申请日：2024-05-07
Applicant: RTX Corporation
Inventor： Lawrence A. Binek , Jesse R. Boyer
CPC classification number: F02K1/80 , B33Y80/00 , B33Y10/00 , F05D2220/323 , F05D2230/31 , F05D2230/60 , F05D2240/128
Abstract: An exhaust duct for an engine includes an outer exhaust duct and a nested exhaust duct capable of having at least two configurations. The nested exhaust duct is circumferentially surrounded by the outer exhaust duct for a first length of the nested exhaust duct in a first configuration. The nested exhaust duct is circumferentially surrounded by the outer exhaust duct for a second length of the nested exhaust duct in a second configuration, which is less than the first length.
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公开(公告)号：US12065985B2
公开(公告)日：2024-08-20
申请号：US18030151
申请日：2021-10-04
Applicant: SAFRAN CERAMICS
Inventor： Thierry Guy Xavier Tesson , Christophe Jean François Thorel , Christophe Paul Aupetit , Thierry Jacques Albert Le Docte , Philippe Avenel
CPC classification number: F02K1/04 , F01D25/30 , F02K1/805 , F02K1/827 , F05D2240/55 , F05D2260/96
Abstract: The present invention relates to an assembly for a turbomachine turbine extending along an axis (X), comprising: —an ejection cone (100) comprising a radially outer annular wall (102) defining a flow duct for a flow of hot gases and a sound box radially arranged inside the outer annular wall (102), the sound box comprising a radially inner annular wall (104), —a connecting member (106) intended to be axially inserted between the exhaust housing and the ejection cone (100), the connecting member (106) comprising an upstream annular flange (108) intended to be attached to the exhaust housing and a plurality of downstream securing tabs (110) connected to the inner annular wall (104), —an annular sealing shroud (112) comprising an upstream portion surrounding the securing tabs (110) of the connecting member (106) so as to cover the spaces circumferentially located between the securing tabs (110) and axially located between the upstream annular flange (108) of the connecting member (106) and the radially inner annular wall (104).
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公开(公告)号：US20240175408A1
公开(公告)日：2024-05-30
申请号：US18234177
申请日：2023-08-15
Applicant: ROLLS-ROYCE plc
Inventor： Jack F COLEBROOKE
CPC classification number: F02K1/1207 , F02K1/002 , F02K1/15 , F02K1/80 , F05D2220/323 , F05D2250/231 , F05D2250/311
Abstract: An exhaust nozzle for a gas turbine engine includes: an exhaust duct configured to receive an exhaust flow of gas from a combustor of the engine; a first flap rotatably coupled to the exhaust duct for rotation about a first axis; a first actuator configured to actuate the first flap about the first axis between a first inner and a first outer position; a second flap rotatably coupled to the exhaust duct for rotation about a second axis; and a second actuator configured to actuate the second flap about the second axis between a second inner and a second outer position. The first and second flaps at least in part define a passageway configured to convey the exhaust flow of gas to an exterior of the gas turbine engine. The first and second axes of rotation are coaxial. Also provides is a method of operating an exhaust nozzle.
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Patent Agency Ranking
公开(公告)号：US11959437B2
公开(公告)日：2024-04-16
申请号：US18251798
申请日：2021-11-03
Applicant: SAFRAN NACELLES , SAFRAN CERAMICS
Inventor： Jean-Philippe Joret , Vincent Devanlay , Fabien Bravin , Thomas Vandellos
Abstract: An assembly for a turbomachine nozzle having a longitudinal axis (X) includes an exhaust cone with an annular outer wall for guiding a primary air flow and an annular chamber placed radially inside said annular outer wall. The annular chamber includes an annular inner wall placed radially inside the annular outer wall of the exhaust cone. An exhaust case is placed upstream of the ejection cone. A connecting member is interposed longitudinally between the exhaust case and the exhaust cone and fastened to the exhaust case and to the annular inner wall. The assembly further includes elastic means configured to deform radially and prestressed radially between the annular outer wall and the connecting member.
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公开(公告)号：US20240101263A1
公开(公告)日：2024-03-28
申请号：US18217182
申请日：2023-06-30
Applicant: Rohr, Inc.
Inventor： Pratap MALLAMPATI , Sree Divya POCHIMIREDDY
CPC classification number: B64D29/08 , F02K1/805 , F02K3/06 , B64D2033/0286
Abstract: An assembly for an aircraft propulsion system includes an upstream cowl and a downstream cowl. The upstream cowl extends axially from a first upstream end to a first downstream end. The upstream cowl includes an inner barrel panel, an outer barrel panel, and a bulkhead. The bulkhead extends radially between and connects the inner barrel panel and the outer barrel panel at the first downstream end. The downstream cowl extends axially from a second upstream end to a second downstream end. The downstream cowl includes a cowl panel and a seal assembly. The seal assembly includes a seal frame and a seal member. The seal frame is mounted to the bulkhead. The seal member is mounted to the cowl panel. The seal member includes a first radial portion projecting away from the cowl panel. The first radial portion is located at the second upstream end.
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公开(公告)号：US11859509B2
公开(公告)日：2024-01-02
申请号：US16395798
申请日：2019-04-26
Applicant: General Electric Company
Inventor： Bernard James Renggli
IPC: F01D25/26 , F01D25/00 , F01D25/24 , F02K1/04 , F02K1/80 , C04B35/80 , B32B3/06 , B32B3/26 , B32B5/26 , F01D25/28
CPC classification number: F01D25/26 , B32B3/06 , B32B3/266 , B32B5/26 , C04B35/80 , F01D25/005 , F01D25/243 , F01D25/28 , F02K1/04 , F02K1/80 , B32B2260/023 , B32B2260/046 , B32B2262/105 , B32B2605/18 , C04B2235/48 , C04B2235/616 , F05D2230/22 , F05D2230/31 , F05D2230/60 , F05D2260/31 , F05D2300/175 , F05D2300/603 , F05D2300/6033 , F16B2200/506
Abstract: 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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公开(公告)号：US20230407813A1
公开(公告)日：2023-12-21
申请号：US18251860
申请日：2021-11-03
Applicant: SAFRAN NACELLES
Inventor： Jean-Philippe JORET , Vincent DEVANLAY , Fabien BRAVIN , Hélène MALOT
Abstract: An assembly for a turbomachine includes an exhaust cone and an exhaust casing having an annular inner shell. The exhaust cone and the exhaust casing can extend about a first axis, the exhaust cone can have an outer surface extending in the projection of the inner shell, the exhaust cone can be connected to the exhaust casing by means of a flange, the flange having an upstream portion fastened to the exhaust casing and lugs extending downstream from said upstream portion, and the exhaust cone can be fastened to the lugs. The flange can be sectorized and include of a plurality of angular sectors arranged so as to be circumferentially adjacent, with each flange sector having at least one lug extending rectilinearly along a second axis parallel to the first axis.
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公开(公告)号：US11746703B2
公开(公告)日：2023-09-05
申请号：US17369677
申请日：2021-07-07
Applicant: General Electric Company
Inventor： Michael Anthony Ruthemeyer , Darrell Glenn Senile , Bernard James Renggli , Randy Lee Lewis
Abstract: A gas turbine engine assembly includes first and second annular members having different first and second thermal expansion coefficients connected together with dual arm V brackets. Brackets include first and second arms angularly spaced apart from a bracket centerline and extending axially away from bracket bases attached to a first one of the first and second annular members. Arms are attached to a second one of the first and second annular members. A turbine frame includes struts extending between outer and inner rings. An annular mixer and centerbody substantially made from a ceramic matrix composite materials is connected to and supported by the outer and inner rings with first and second sets respectively of the dual arm V brackets. Bracket bases of the first and second sets are attached to the outer and inner rings respectively. Arms of the first and second sets are attached to mixer and centerbody respectively.
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