公开(公告)号：US12000360B2

公开(公告)日：2024-06-04

申请号：US17856612

申请日：2022-07-01

申请人： RTX CORPORATION

发明人： Lawrence A. Binek ,  Jesse R. Boyer

IPC分类号： F02K1/80 ,  B33Y10/00 ,  B33Y80/00 ,  F01N1/16 ,  F01N13/08 ,  F02K1/08 ,  F02K1/09

CPC分类号： F02K1/80 ,  B33Y80/00 ,  B33Y10/00 ,  F05D2220/323 ,  F05D2230/31 ,  F05D2230/60 ,  F05D2240/128

摘要： 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.

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

发明人： Jean-Philippe JORET ,  Vincent DEVANLAY ,  Fabien BRAVIN ,  Boualem MERABET

IPC分类号： F02K1/04 ,  F02K1/80

CPC分类号： F02K1/04 ,  F02K1/80

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：US11788491B1

公开(公告)日：2023-10-17

申请号：US17863993

申请日：2022-07-13

申请人： General Electric Company

发明人： Nicholas Direnzi ,  John Philip McKay ,  Apostolos Karafillis ,  David L. Dawson ,  Rosa Nemec

IPC分类号： F02K1/80

CPC分类号： F02K1/80 ,  F05D2220/323 ,  F05D2260/31 ,  F05D2300/6033

摘要： Systems and methods for attaching a protective liner to a an aircraft engine component having a different coefficient of thermal expansion in comparison to the protective liner include a mounting member configured to be mounted to the aircraft engine component and an attachment member configured to be attached to the protective liner. The mounting member and the attachment member are coupled to each other such that a portion of the mounting member is received within a portion of the attachment member and such that the mounting member is permitted to move with both radial and rotational freedom relative to the attachment member.

公开(公告)号：US11772809B2

公开(公告)日：2023-10-03

申请号：US17535995

申请日：2021-11-27

申请人： Airbus Defence and Space GmbH

发明人： Wolfgang Stangl ,  Robert Osterhuber ,  Philipp Ernstberger

IPC分类号： F02K1/12 ,  B64D33/04 ,  B64D27/20 ,  B64D29/04 ,  B64C1/16 ,  F02K1/00 ,  F02K1/80

CPC分类号： B64D33/04 ,  B64C1/16 ,  B64D27/20 ,  B64D29/04 ,  F02K1/002 ,  F02K1/006 ,  F02K1/1223 ,  F02K1/80

摘要： A fuselage for an aircraft. The fuselage has a control element with an integrated engine outlet. The control element is integrated at a rear end of the fuselage, so that the control element terminates flush with an outer skin of the fuselage in a circumferential direction of the fuselage. An outer wall of the control element surrounds the engine outlet wherein the engine outlet is directed towards an open rear side of the control element. The control element is connected to the fuselage such that the control element jointly the engine outlet is pivotable about a rotation axis with respect to the fuselage. The rotation axis runs transversely to a longitudinal direction of the fuselage and the control element functions as a tailplane when pivoting about the rotation axis.

公开(公告)号：US10077681B2

公开(公告)日：2018-09-18

申请号：US14759623

申请日：2013-12-13

申请人： UNITED TECHNOLOGIES CORPORATION

发明人： Lon H. Preston

IPC分类号： F01D25/28 ,  F23R3/00 ,  B23P15/00 ,  F02K9/34 ,  F23R3/60 ,  F02K1/82 ,  F02C7/20 ,  F02K1/80

CPC分类号： F01D25/28 ,  B23P15/00 ,  F02C7/20 ,  F02K1/80 ,  F02K1/82 ,  F02K1/822 ,  F02K9/34 ,  F02K9/343 ,  F02K9/346 ,  F05D2230/642 ,  F23R3/005 ,  F23R3/60 ,  Y02T50/675 ,  Y10T29/49325

摘要： Hanger assemblies for coupling heat shield liners to cases of gas turbine engines are disclosed. The disclosed hanger assemblies include a pivoting joint coupled between a first segment and a second segment. The first segment is coupled to the liner by a liner attachment assembly and the second segment is coupled to the case by a case attachment assembly. At least one of the liner attachment assembly or the case attachment assembly permits translational movement of the first or second segments respectively with respect to the liner or case to accommodate for thermal expansion in the axial direction.

公开(公告)号：US10012175B2

公开(公告)日：2018-07-03

申请号：US14291296

申请日：2014-05-30

申请人： The Boeing Company

发明人： Richard Stokes, Jr. ,  Donald Powell ,  Robert Morrow

IPC分类号： F02C1/00 ,  F02K1/76 ,  B64D29/06 ,  F02K1/80

CPC分类号： F02K1/763 ,  B64D29/06 ,  F02K1/80 ,  F05D2230/60 ,  Y02T50/672 ,  Y10T29/49231

摘要： A thrust reverser torque box assembly for an aircraft engine is constructed with a torque tube having a cross section configuration tailored and conducive to carrying torsion and discrete major fittings at opposite ends of the torque tube that connect the torque tube and thrust reverser actuation and reacts loading due to reverse thrust operation to the aircraft engine fan case.

公开(公告)号：US09938929B2

公开(公告)日：2018-04-10

申请号：US14222134

申请日：2014-03-21

申请人： Rohr, Inc.

发明人： Timothy Gormley

IPC分类号： F02K1/72 ,  F02K1/80

CPC分类号： F02K1/72 ,  F02K1/80 ,  Y02T50/672

摘要： A thrust reverser of a turbofan engine has a translating structure and a blocker door device capable of diverting a bypass flowpath for reversing propulsion direction. The translating structure moves axially between a forward position and a rearward position and thereby drives a compound motion of a blocker door of the blocker door device that moves between a respective stowed state and a deployed state. The compound motion is attributable through the blocker door being pivotally engaged to the translating structure, and through a multi-armed linkage of the device being pivotally engaged between a stationary structure, the blocker door and the translating structure. The linkage is further orientated such that it does not appreciably obstruct the bypass flowpath when the blocker door is in the stowed state.

公开(公告)号：US09879566B2

公开(公告)日：2018-01-30

申请号：US14793465

申请日：2015-07-07

申请人： HONEYWELL INTERNATIONAL INC.

发明人： Mark C. Morris ,  David R. Waldman ,  Donald G. Godfrey ,  Brian G. Baughman ,  Mark McNair ,  Justin C. Mickelsen

IPC分类号： F01D25/28 ,  F16L27/111 ,  F16L47/18 ,  F02K1/80 ,  F02C7/32

CPC分类号： F01D25/28 ,  B22F3/1055 ,  B33Y80/00 ,  F02C7/32 ,  F02K1/80 ,  F16L27/111 ,  F16L47/18 ,  Y02P10/295

摘要： A coupling apparatus for use in sealingly connecting a first fluid flow path to a second fluid flow path. The coupling apparatus includes a rigid fluid flow channel having a first end and a second end, wherein the fluid flow channel is substantially rigid in an axial direction and a radial direction, a first sealing terminus that is rigidly connected to the first end and that is configured for sealing with the first fluid flow path, and a second sealing terminus that is slidingly disposed about the second end such that the second sealing terminus is configured for relative movement with respect to the second end, and wherein the second sealing terminus is further configured for sealing with the second fluid flow path. The coupling apparatus further includes a flexible coupler connected to both the first sealing terminus and the second sealing terminus and surrounding the fluid flow channel, wherein the coupler is relatively more flexible in the axial direction and the radial direction as compared to the fluid flow channel.

公开(公告)号：US09850850B2

公开(公告)日：2017-12-26

申请号：US14061469

申请日：2013-10-23

申请人： ROHR, INC.

发明人： Michael Aten

IPC分类号： F02K1/80 ,  F02K1/34 ,  B64D29/06 ,  F02K1/72 ,  F02K1/82 ,  F02C7/20

CPC分类号： F02K1/80 ,  B64D29/06 ,  B64D33/06 ,  F02C7/20 ,  F02K1/72 ,  F02K1/827 ,  F05D2250/11 ,  F05D2250/292 ,  F05D2260/96

摘要： A thrust reverser track beam is disclosed. The thrust reverser track beam may comprise a recess defined by a reception surface and/or a perimeter surface surrounding the reception surface and extending away from the reception surface, wherein the reception surface and the perimeter surface bound a recess that is configured to receive a noise suppressing structure. The thrust reverser track beam may further comprise the noise suppressing structure. The recess is generally triangular in shape and may extend away from a plane. The noise suppressing structure may be generally triangular in shape and may extend away from a plane. The noise suppressing structure may be coupled within the recess of the track beam and/or to the track beam.

公开(公告)号：US09739235B2

公开(公告)日：2017-08-22

申请号：US14222192

申请日：2014-03-21

申请人： Rohr, Inc.

发明人： Timothy Gormley

IPC分类号： F02K1/72 ,  F02K1/76 ,  F02K1/80

CPC分类号： F02K1/72 ,  F02K1/763 ,  F02K1/80 ,  F05D2260/50

摘要： A thrust reverser of a turbofan engine has a stationary structure, a translating structure capable of moving linearly between a forward position and an aft position, a translating member capable of moving linearly between a forward condition and an aft condition when the translating structure is in the aft position, and a blocker door device engaged pivotally to the translating member and capable of rotating from a stowed state when the translating member is in the forward position and to a deployed state when the translating member is in the aft condition. When the thrust reverser is stowed, the blocker door device is located radially outward from a pressure sleeve of the translating structure and does not substantially obstruct flow in a flowpath defined at least in-part by the pressure sleeve.