公开(公告)号：US11773623B2

公开(公告)日：2023-10-03

申请号：US17220442

申请日：2021-04-01

Applicant: ROHR, INC.

Inventor： Jose Roberto Aguilar Ante ,  Jaime Francisco Salazar Ibarra

IPC: E05B41/00 ,  B64D29/06 ,  E05B15/00

CPC classification number: E05B41/00 ,  B64D29/06 ,  E05B15/0086 ,  E05Y2900/502 ,  F05B2240/14

Abstract: A latch handle arrangement includes a latch handle body and a removable insert. The latch handle body comprises a first sidewall, a second sidewall, and a transverse wall extending from the first sidewall to the second sidewall. The latch handle body further comprises one or more apertures disposed in the latch handle body. The removable insert is configured to be coupled to the latch handle body. The removable insert comprises an insert body and one or more bosses protruding from the insert body into the respective apertures disposed in the latch handle body, wherein the boss(es) are visible from an external surface of the latch handle body.

公开(公告)号：US20230286661A1

公开(公告)日：2023-09-14

申请号：US18040444

申请日：2021-08-02

Applicant: MTU Aero Engines AG

Inventor： Hermann Klingels

IPC: B64D27/18 ,  B64D27/26 ,  B64D33/10 ,  B64D29/06 ,  F02C7/141 ,  F02C3/30

CPC classification number: B64D27/18 ,  B64D27/26 ,  B64D33/10 ,  B64D29/06 ,  F02C7/141 ,  F02C3/305 ,  F05D2220/323 ,  F05D2260/213 ,  F05D2270/08

Abstract: The present invention relates to an aircraft comprising at least one wing, at least one flight propulsion drive, and a retainer, particularly an engine pylon, which interconnects the wing and the flight propulsion drive. The aircraft comprises at least one heat exchanger for cooling exhaust gas of the fight propulsion drive and/or at least one water removal channel having at least one removal apparatus for removing water from exhaust gas of the flight propulsion drive, especially after the exhaust gas has flowed through the heat exchanger. The removal apparatus is disposed on, more particularly in, the retainer or is connected to the wing by means of the retainer, and/or the flight propulsion drive is fastened to the retainer by means of at least one flight propulsion drive suspension means, and the heat exchanger is fastened, independently thereof, to the retainer by means of at least one heat exchanger suspension means.

公开(公告)号：US11753176B2

公开(公告)日：2023-09-12

申请号：US17558213

申请日：2021-12-21

Applicant: Airbus Operations (S.A.S.)

Inventor： Alexis Courpet ,  Jean Geliot ,  Arnaud Bourhis

IPC: B64D27/26 ,  B64D29/06 ,  B64D29/08

CPC classification number: B64D27/26 ,  B64D29/06 ,  B64D29/08 ,  B64D2027/264

Abstract: A forward secondary structure for a mounting pylon for a turbomachine, the forward secondary structure extending from upstream to downstream along a longitudinal axis and having a chassis clad with an aerodynamic fairing. The aerodynamic fairing includes two adjacent cowls each having an upstream portion, where each of the cowls extends lengthwise along the longitudinal direction and includes in its upstream portion a system for articulating the cowl to the chassis, by which system the cowl can pivot with respect to the chassis about an axis of rotation normal to the longitudinal axis, between a closed position in which all of an inner face of the cowl is pressed against the chassis and an open position in which the cowl frees up an opening in the forward secondary structure.

公开(公告)号：US11746726B2

公开(公告)日：2023-09-05

申请号：US17307570

申请日：2021-05-04

Applicant: Rohr, Inc.

Inventor： Adam Saunders ,  Bryce T. Kelford ,  Travis M. Frazier ,  Richard Haslim ,  Richard S. Alloway ,  Vijay V. Pujar

IPC: F02K1/52 ,  B64D29/06 ,  F02K1/80 ,  F02K1/04 ,  F02K1/82 ,  F02K1/38 ,  B64D27/26 ,  B64D27/18 ,  F02K3/06

CPC classification number: F02K1/52 ,  B64D27/18 ,  B64D29/06 ,  F02K1/805 ,  F02K3/06 ,  B64D27/26 ,  F05D2220/323 ,  F05D2240/128

Abstract: An assembly is provided for an aircraft propulsion system. This assembly includes a nozzle extending axially along and circumferentially about an axial centerline. The nozzle includes a nozzle panel and a nozzle fairing fixedly connected to the nozzle panel at an axial end of the nozzle. The nozzle is configured with an internal flow passage radially between the nozzle panel and the nozzle fairing. The internal flow passage extends axially within the nozzle to an outlet between the nozzle panel and the nozzle fairing at the axial end of the nozzle.

公开(公告)号：US20230265694A1

公开(公告)日：2023-08-24

申请号：US18172887

申请日：2023-02-22

Applicant: Airbus Operations SAS

Inventor： Wolfgang BROCHARD ,  Laurent CAZEAUX ,  Benjamin VIGNOBOUL

IPC: E05C1/00 ,  B64D29/06

CPC classification number: E05C1/006 ,  B64D29/06

Abstract: A locking mechanism situated in an inner zone and comprising at least one component that is adjustable in a longitudinal direction and that is linked to a support by a link having a rod secured to the adjustable component. The link includes a guideway link, linking the rod and the support, and an adjustment system. The adjustment system comprises a pivoting control pivoting on itself and having a first end accessible from an outer zone, an intermediate piece configured to pivot on itself, an angle transmission converting a pivoting movement of the pivoting control into a pivoting movement of the intermediate piece, and a helical link converting a pivoting movement of the intermediate piece into a translational movement of the rod. The locking mechanism allows for adjustment from the outer zone. An aircraft comprising at least one such locking mechanism is also provided.

公开(公告)号：US20230250682A1

公开(公告)日：2023-08-10

申请号：US18118739

申请日：2023-03-07

Applicant: QRP, Inc.

Inventor： Joseph B Newell

IPC: E05C19/14

CPC classification number: E05C19/145 ,  B64D29/06

Abstract: A latch is operable between a disengaged position and an engaged position releasably connecting a latch mounting pin on a first static structural element to a keeper on a second, movable structural element. The latch includes means for adjusting the throw of the hook to accommodate different distances between the latch mounting pin and the keeper due to manufacturing tolerances or different applications. The latch has a tension mechanism, a hook connected to the tension mechanism, and a handle pivotably connected to the tension mechanism and operable to actuate the tension mechanism between engaged and disengaged positions with the keeper. The latch is operable between the engaged and disengaged positions by rotating the handle between a closed position and an open position.

公开(公告)号：US11686272B2

公开(公告)日：2023-06-27

申请号：US17471933

申请日：2021-09-10

Applicant: Rohr, Inc.

Inventor： Michael Aten

IPC: F02K1/12 ,  B64D29/06 ,  B64D29/08 ,  B64D33/02

CPC classification number: F02K1/12 ,  B64D29/06 ,  B64D29/08 ,  B64D33/02

Abstract: A propulsion system assembly includes a variable area inlet and an inlet duct. The variable area inlet includes an outer airflow inlet passage, an inner airflow inlet passage, an inlet structure and a center body structure. The outer airflow inlet passage is between the inlet structure and the center body structure. The inner airflow inlet passage is formed within the center body structure. The center body structure includes a valve configured to regulate air flow through the inner airflow inlet passage. The valve includes a first door configured to pivot between a closed position and an open position. The inlet duct is configured to receive air from the outer airflow inlet passage when the first door is in the closed position. The inlet duct is configured to receive air from the outer airflow inlet passage and the inner airflow inlet passage when the first door is in the open position.

公开(公告)号：US20230192308A1

公开(公告)日：2023-06-22

申请号：US18069282

申请日：2022-12-21

Applicant: SAFRAN NACELLES

Inventor： Romain GARDEL ,  Pierre-Alain REBOUL ,  Jérôme CORFA ,  Jean-Philippe JORET ,  Thomas MARLAY ,  Matthieu MENIELLE

IPC: B64D29/06 ,  B64D29/08 ,  F02K1/56

CPC classification number: B64D29/06 ,  B64D29/08 ,  F02K1/566

Abstract: A nacelle for an aircraft propulsion assembly includes an actuator, a secondary door subject to the actuator and contributing to defining an external aerodynamic surface of the nacelle in a first position, a main door contributing to defining the external aerodynamic surface and including a recess that the actuator passes through in a deployed position but not in a retracted position, and a flap connected to the main door. The flap is movable between a closed position wherein the flap closes off at least a first region of the recess through which the actuator passes in the deployed position whereby the flap contributes to defining the external aerodynamic surface, and an open position wherein the flap is moved away from the recess so as to clear the passage for the actuator through the first region of the recess.

公开(公告)号：US20230182913A1

公开(公告)日：2023-06-15

申请号：US17999180

申请日：2021-05-18

Applicant: SAFRAN NACELLES

Inventor： Patrick André BOILEAU ,  Jean-Philippe JORET ,  Vincent Jean-François PEYRON ,  Gina FERRIER

IPC: B64D29/08 ,  B64D29/06 ,  F02K1/72

CPC classification number: B64D29/08 ,  B64D29/06 ,  F02K1/72

Abstract: A nacelle for a propulsion assembly, the nacelle including a front internal structure having a framework formed of longitudinal beams and including removable, dismountable or retractable panels which are provided to facilitate the access for maintenance to the parts of the motor shrouded by these panels.

公开(公告)号：US11661173B2

公开(公告)日：2023-05-30

申请号：US16507470

申请日：2019-07-10

Applicant: Airbus Operations S.A.S.

Inventor： Alain Porte ,  Francois Pons ,  Arnaud Bourhis ,  Julien Sentier

IPC: B64C7/02 ,  B64D29/06 ,  F01D25/24

CPC classification number: B64C7/02 ,  B64D29/06 ,  F01D25/24

Abstract: An aircraft nacelle air intake includes sectors each having a lip forming portion, an outer panel forming portion and an inner panel forming portion. The outer panel forming portions and lip forming portions are formed by a continuous one-piece wall. At at least one junction between two adjacent sectors, an opening and a hatch are provided between the outer panel forming portions of the sectors. The inner panel forming portions and the lip forming portions of the sectors are edge to edge and fixed to each other by fixing devices accessible from the inside of the sectors and invisible from outside of the sectors. A maintenance method in which, when a zone of a sector is damaged, the sector concerned is removed as a whole and is replaced by a new of “recycled” sector is also described.