公开(公告)号：US20240417089A1

公开(公告)日：2024-12-19

申请号：US18740984

申请日：2024-06-12

Applicant: Airbus Operations SAS

Inventor： Thomas DEFORET ,  Frédéric JOURNADE ,  Mathieu MAHE ,  Antoine CLAVEYROLLAS ,  Mathieu KALETA ,  Eric RENAUD

IPC: B64D27/40 ,  B64D27/18

Abstract: A propulsion assembly for an aircraft, the propulsion assembly having a jet engine having a fan casing and a central casing around a longitudinal axis and having a vertical median plane passing through the longitudinal axis, an attachment pylon having a rigid structure that takes the form of a box that has a front wall and an upper spar extending forwardly in respect to the front wall, a front engine attachment fixed between an upper area of the central casing and a lower end of the front wall, and a complementary front engine attachment fixed between an upper area of the fan casing and a front end of the upper spar.

公开(公告)号：US20240417086A1

公开(公告)日：2024-12-19

申请号：US18740953

申请日：2024-06-12

Applicant: Airbus Operations SAS

Inventor： Thomas DEFORET ,  Frédéric JOURNADE ,  Mathieu MAHE ,  Antoine CLAVEYROLLAS ,  Mathieu KALETA ,  Eric RENAUD

IPC: B64D27/40 ,  B64D27/18

Abstract: A propulsion assembly for an aircraft, the propulsion assembly having a jet engine having a fan casing and a central casing around a longitudinal axis and having a vertical median plane passing through the longitudinal axis, an attachment pylon having a rigid structure that takes the form of a box that has a front wall and an upper spar extending forwardly in respect to the front wall, a front engine attachment fixed between an upper area of the fan casing and a front end of the upper spar, and a complementary front engine attachment fixed between an upper area of the central casing and a lower end of the front wall.

公开(公告)号：US20240417085A1

公开(公告)日：2024-12-19

申请号：US18740948

申请日：2024-06-12

Applicant: Airbus Operations SAS

Inventor： Thomas DEFORET ,  Frédéric JOURNADE ,  Mathieu MAHE ,  Antoine CLAVEYROLLAS ,  Mathieu KALETA ,  Eric RENAUD

IPC: B64D27/40 ,  B64D27/18

Abstract: A propulsion assembly for an aircraft, the propulsion assembly having a jet engine having a fan casing and a central casing around a longitudinal axis and having a vertical median plane passing through the longitudinal axis, an attachment pylon having a rigid structure that takes the form of a box that has a front wall and an upper spar extending forwardly in respect to the front wall, a front engine attachment fixed between an upper area of the fan casing and a front end of the upper spar, and a complementary front engine attachment fixed between an upper area of the central casing and a lower end of the front wall.

公开(公告)号：US20240417088A1

公开(公告)日：2024-12-19

申请号：US18740971

申请日：2024-06-12

Applicant: Airbus Operations SAS

Inventor： Thomas DEFORET ,  Mathieu MAHE ,  Mathieu KALETA ,  Eric RENAUD

IPC: B64D27/40 ,  A62C3/08 ,  A62C35/68

Abstract: A propulsion assembly for an aircraft, the propulsion assembly having a jet engine, an attachment pylon having a rigid structure, and an extinguishing system. The extinguishing system is located in a front position relative to the rigid structure, the extinguishing system being positioned between the rigid structure and the jet engine.

公开(公告)号：US20240417087A1

公开(公告)日：2024-12-19

申请号：US18740961

申请日：2024-06-12

Applicant: Airbus Operations SAS

Inventor： Thomas DEFORET ,  Frédéric JOURNADE ,  Mathieu MAHE ,  Antoine CLAVEYROLLAS ,  Mathieu KALETA ,  Eric RENAUD

IPC: B64D27/40 ,  B64D27/18

Abstract: A propulsion assembly for an aircraft, the propulsion assembly having a jet engine having a fan casing and a central casing around a longitudinal axis and having a vertical median plane passing through the longitudinal axis, an attachment pylon having a rigid structure that takes the form of a box that has a front wall and an upper spar extending forwardly in respect to the front wall, a front engine attachment fixed between an upper area of the central casing and a lower end of the front wall, and a complementary front engine attachment fixed between an upper area of the fan casing and a front end of the upper spar.

公开(公告)号：US20240400216A1

公开(公告)日：2024-12-05

申请号：US18673984

申请日：2024-05-24

Applicant: Airbus Operations SAS

Inventor： Eric RENAUD ,  Thomas DEFORET ,  Mathieu KALETA ,  Antoine CLAVEYROLLAS ,  Mathieu MAHE ,  Ginesa TORRES LOPEZ

IPC: B64D29/06 ,  F01D25/24

Abstract: A propulsion assembly comprising a fan casing and a nacelle which comprises an air inlet which is connected to the front end of the fan casing, an intermediate portion which is positioned around the fan casing and a rear portion which cooperates with the rear end of the fan casing. The intermediate portion comprises at least one aerodynamic panel which extends from a front edge which is attached to the air inlet as far as a rear edge which is attached to the rear portion and at least one intermediate radial support comprising an internal edge which is connected to the fan casing and an external edge which is connected to the aerodynamic panel, this panel comprising a front edge which is connected to the air inlet by a first connection system. Also an aircraft with such a propulsion assembly.