公开(公告)号：US10676203B2

公开(公告)日：2020-06-09

申请号：US15834605

申请日：2017-12-07

Applicant: Airbus Operations S.A.S. ,  AIRBUS SAS

Inventor： Alain Porte ,  Patrick Oberle ,  Gregory Albet

IPC: B64D33/02 ,  B64F5/40 ,  F02C7/04

Abstract: An air input structure includes an air input lip and a front reinforcement frame placed inside the air input lip. The front part of the air input lip has a plurality of segments distributed angularly along the leading edge of the air input lip, two adjacent segments being separated by an intermediate part having an excess thickness. Each segment has four edges, each having an excess thickness relative to the rest of the segment.

公开(公告)号：US20180170568A1

公开(公告)日：2018-06-21

申请号：US15834605

申请日：2017-12-07

Applicant: Airbus Operations S.A.S. ,  AIRBUS SAS

Inventor： Alain Porte ,  Patrick Oberle ,  Gregory Albet

IPC: B64D33/02 ,  B64F5/40

Abstract: An air input structure includes an air input lip and a front reinforcement frame placed inside the air input lip. The front part of the air input lip has a plurality of segments distributed angularly along the leading edge of the air input lip, two adjacent segments being separated by an intermediate part having an excess thickness. Each segment has four edges, each having an excess thickness relative to the rest of the segment. Thus, the air input lip has a lighter structure.

公开(公告)号：US11745887B2

公开(公告)日：2023-09-05

申请号：US17091604

申请日：2020-11-06

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

Inventor： Alain Porte ,  Jacques Lalane ,  Arnaud Bourhis ,  Florent Mercat

IPC: B64D33/02 ,  G10K11/172 ,  G10K11/168

CPC classification number: B64D33/02 ,  G10K11/168 ,  G10K11/172 ,  B64D2033/0206

Abstract: An acoustic panel for an aircraft nacelle includes, from a central axis of the nacelle to the exterior thereof, a resistive skin perforated with sound-absorbing micro-perforations, a first attenuation stage, a septum perforated with holes, a second attenuation stage, and a back skin configured to provide the mechanical strength of the acoustic panel. The septum is a planar wall having a thickness greater than that of the resistive skin, preferably greater than 4 mm. Such a panel is configured to attenuate several frequency ranges one of which being a low-frequency range, while optimizing the weight, the cost and the air intake functions. The thickness of the septum, the dimensions of the holes in the septum, the OAR of the septum and the height of the second attenuation stage are adjusted to match the mean attenuated low frequency to the vibration frequency of the aircraft engine.

公开(公告)号：US11384688B2

公开(公告)日：2022-07-12

申请号：US16456500

申请日：2019-06-28

Applicant: AIRBUS OPERATIONS (S.A.S.)

Inventor： Arnaud Bourhis ,  François Pons ,  Alain Porte

IPC: F02C7/055 ,  B64D33/02

Abstract: An air intake structure for a nacelle of an aircraft is disclosed having an air intake lip with a U-shaped section open towards the rear, an acoustic panel that extends the air intake lip towards the rear and on an inner side, an outer panel extending the air intake lip towards the rear and on an outer side, and a rear strengthening frame fixed between the outer panel and the acoustic panel, where the rear strengthening frame partly defines an inner volume that is immediately in front of the rear strengthening frame. The air intake structure comprises an impact absorber element positioned in the inner volume and the impact absorber element assumes the form of a structure that is deformable during an impact and that is at least partially filled with a fluid. The impact absorber element is a flexible shroud filled with a pressurized gas.

公开(公告)号：US20210040867A1

公开(公告)日：2021-02-11

申请号：US16985413

申请日：2020-08-05

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

Inventor： Alain Porte ,  Julien Sentier ,  Clément Breton

IPC: F01D25/28 ,  B64D33/02 ,  B64D29/00 ,  F01D25/24 ,  F02C7/20

Abstract: An anterior part of a nacelle of an aircraft propulsion unit. A rigidifying frame annular about a longitudinal axis of extension of the nacelle is at the rear end of the anterior part. An annular shield is in front of the rigidifying frame and connects an internal peripheral edge of the rigidifying frame to an internal structure. The shield has a portion extending towards the external panel beyond the internal peripheral edge of the rigidifying frame, the portion forming a non-zero angle with respect to the rigidifying frame to form a free space with respect to the rigidifying frame behind the portion. The shield can thus deform in the event of an impact of a foreign object entering through the air inlet lip, without the rigidifying frame itself being deformed, thereby absorbing all or some of the impact energy. A nacelle can have such an anterior part, and an aircraft can have such a nacelle.

公开(公告)号：US20180201387A1

公开(公告)日：2018-07-19

申请号：US15847207

申请日：2017-12-19

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

Inventor： Alain Porte ,  Eric Haramburu ,  Patrick Oberle ,  Grégory Albet ,  Vincent Billerot ,  Frédéric Piard ,  Franck Oundjian

IPC: B64D33/02 ,  F02C7/045 ,  F02C7/047

CPC classification number: B64D33/02 ,  B64D2033/0206 ,  B64D2033/0233 ,  B64D2033/0286 ,  F02C7/045 ,  F02C7/047 ,  F05D2220/323 ,  F05D2250/75 ,  F05D2260/83 ,  F05D2260/96 ,  Y02T50/672

Abstract: An aircraft nacelle air intake structure including an air intake lip with a U-shaped section to ensure air is shared between an inner face and an outer face. An acoustic panel is on the intake lip rear on the side of the inner face level with a first assembly point. An outer panel is on the intake lip rear on the side of the outer face level with a second assembly point. A front reinforcing frame on the intake lip inside is fixed to the air intake lip on the side of the inner face level with a first fixing point and on the side of the outer face level with a second fixing point. The length of the chord between the stop point and each fixing point is between ⅓ and ⅙ of the total chord between the stop point and the assembly point.

公开(公告)号：US20180149113A1

公开(公告)日：2018-05-31

申请号：US15823053

申请日：2017-11-27

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

Inventor： Thierry Surply ,  Alain Porte ,  Patrick Oberle ,  Eric Haramburu ,  Thomas Sauvalle ,  Benoit Letay ,  Frédéric Piard ,  Vincent Billerot ,  Franck Oundjian

IPC: F02K1/70 ,  F02K1/76

CPC classification number: F02K1/70 ,  F01D25/24 ,  F02K1/72 ,  F02K1/763 ,  F05D2220/323 ,  F05D2250/42

Abstract: A nacelle has a fixed cowl and a mobile cowl, which is movable along a translation path between closing and opening positions, a window delimited by the fixed cowl and the mobile cowl and open between an airflow and exterior of the nacelle, a reverser flap rotatably mounted to move between closed and open positions, and a drive mechanism configured to control passage of the reverser flap between the closed and open positions as the mobile cowl moves between the closed and open positions. From the closing/closed positions, the drive mechanism assures a translation of the mobile cowl and a rotation of the reverser flap toward their respective opening/open positions. From the open/opening positions, the drive mechanism assures a rotation of the reverser flap and a translation of the mobile cowl toward their respective closed/closing position. In some embodiments, the nacelle further includes an additional, or second, flap.

公开(公告)号：US12023879B2

公开(公告)日：2024-07-02

申请号：US16584555

申请日：2019-09-26

Applicant: AIRBUS OPERATIONS S.A.S.

Inventor： Alain Porte ,  Jacques Lalane ,  Hassan Menay

IPC: B29C70/54 ,  B29C65/02 ,  B29C70/88 ,  B32B37/06 ,  B64D33/02 ,  B32B38/04

CPC classification number: B29C70/882 ,  B29C65/02 ,  B29C70/545 ,  B32B37/06 ,  B64D33/02 ,  B32B2038/047 ,  B32B2305/02 ,  B32B2305/07 ,  B32B2305/38 ,  B32B2313/04 ,  B64D2033/0206 ,  B64D2033/0233

Abstract: A method for manufacturing deicing acoustic skin for an aircraft acoustic panel, using a fiber spacing device. The manufacturing method includes at least one step for manufacturing a layer assembly having a deicing layer supplied with electrically conductive fibers embedded in a resin and two insulating layers arranged on either side of the deicing layer, and a baking step. The method provides for fitting, during baking, a spacing device on the layer assembly, the spacing device having pins passing through said layer assembly, perforations being produced at the locations of the pins after the withdrawal of the spacing device, the fitting of the spacing device making it possible to produce perforations with desired sizes and shapes, in a simple and effective manner, and with a reduced manufacturing duration.

公开(公告)号：US11679889B2

公开(公告)日：2023-06-20

申请号：US16440214

申请日：2019-06-13

Applicant: Airbus Operations S.A.S.

Inventor： Clément Breton ,  Julien Sentier ,  Frédéric Vinches ,  Alain Porte ,  Wolfgang Brochard

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

CPC classification number: B64D29/06 ,  B64C7/02 ,  F01D25/243 ,  F05D2260/30

Abstract: A nacelle of an aircraft propulsion assembly includes a front section and a main section. The nacelle also includes a junction flange between the front section and the main section including a plurality of deformable damper elements distributed along the inner peripheral edge of a stiffening frame of the nacelle. The damper element allows significant stresses to be absorbed between the engine flange and the stiffening frame. This configuration is particularly adapted to large nacelles. An aircraft propulsion assembly including such a nacelle is also described.

公开(公告)号：US11066994B2

公开(公告)日：2021-07-20

申请号：US16586075

申请日：2019-09-27

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

Inventor： Alain Porte ,  Jacques Lalane ,  François Pons

IPC: F02C7/045 ,  B64D33/02 ,  G10K11/16

Abstract: An assembly including two juxtaposed acoustic panels. Resistive faces of the acoustic panels are in the continuation of one another. A first resistive face extends as far as the first end wall of a first panel. The first end wall is in contact with a second end wall of a second panel in the region of the first resistive face and of the second resistive face. A connecting piece is interposed between the first end wall and the second end wall over a part of the length thereof so that the connecting piece does not extend as far as the first and second resistive faces. That makes it possible to form an acoustic cladding that is continuous, exhibiting no non-acoustic zone or reduced-acoustic zone at the junction between the acoustic panels of which it is formed. A nacelle of an aircraft propulsion unit is one application.