公开(公告)号：US20160221682A1

公开(公告)日：2016-08-04

申请号：US15008593

申请日：2016-01-28

Applicant: Airbus Operations SAS

Inventor： Olivier Pautis ,  Rohan Nanda

IPC: B64D27/26 ,  B64D27/18

CPC classification number: B64D27/26 ,  B64D27/18 ,  B64D2027/262 ,  B64D2027/268

Abstract: A propulsion assembly includes a turbojet incorporating a fan casing and a central casing around a longitudinal axis, a mounting pylon having a rigid structure, a forward engine attachment interposed between a forward extremity of the rigid structure and an upper part of the fan casing, the upper part being in a vertical median plane (P) passing through the longitudinal axis, an aft engine attachment interposed between a median zone of the rigid structure and an upper aft part of the central casing, and a device for absorbing the thrust forces generated by the turbojet, including two links placed either side of the median plane (P) and hinged, on one hand, forward, on a forward part of the central casing, and on the other, aft, directly on the rigid structure. Such an arrangement enables a reduction of the stresses, and the possibility of designing a simplified rigid structure.

Abstract translation: 推进组件包括涡轮喷气发动机，其包括风扇壳体和围绕纵向轴线的中心壳体，具有刚性结构的安装支架，插入在刚性结构的前端和风扇壳体的上部之间的前部发动机附件， 上部位于通过纵向轴线的垂直中间平面（P）中，插入在刚性结构的中间区域和中央壳体的上部后部之间的后部发动机附件，以及用于吸收由中心壳体产生的推力的装置， 涡轮喷气发动机，包括位于中间平面（P）的任一侧的两个连杆，并且一方面在中心壳体的前部向前并且另一个直接在刚性结构上的后部铰接。 这种布置使得能够减小应力，并且可以设计简化的刚性结构。

公开(公告)号：US09919804B2

公开(公告)日：2018-03-20

申请号：US15008593

申请日：2016-01-28

Applicant: Airbus Operations SAS

Inventor： Olivier Pautis ,  Rohan Nanda

IPC: B64D27/18 ,  B64D27/26

CPC classification number: B64D27/26 ,  B64D27/18 ,  B64D2027/262 ,  B64D2027/268

Abstract: A propulsion assembly includes a turbojet incorporating a fan casing and a central casing around a longitudinal axis, a mounting pylon having a rigid structure, a forward engine attachment interposed between a forward extremity of the rigid structure and an upper part of the fan casing, the upper part being in a vertical median plane (P) passing through the longitudinal axis, an aft engine attachment interposed between a median zone of the rigid structure and an upper aft part of the central casing, and a device for absorbing the thrust forces generated by the turbojet, including two links placed either side of the median plane (P) and hinged, on one hand, forward, on a forward part of the central casing, and on the other, aft, directly on the rigid structure. Such an arrangement enables a reduction of the stresses, and the possibility of designing a simplified rigid structure.

公开(公告)号：US10647440B2

公开(公告)日：2020-05-12

申请号：US15823890

申请日：2017-11-28

Applicant: Airbus Operations SAS

Inventor： Eric Bouchet ,  Jérôme Colmagro ,  Rohan Nanda ,  Misael Hernandez Perez

IPC: B64D27/20 ,  B64D27/26

Abstract: To allow the attachment of an engine of the “Open Rotor Puller” type to the rigid structure of an attachment pylon, an attachment structure comprises a first attachment structure shifted forwards with respect to the center of gravity of the engine and connected to the rigid structure through a pyramid, a second attachment structure laid out at the rear with respect to the first attachment structure and extending in a plane of a first stringer of the rigid structure, and a third attachment structure laid out at the rear with respect to the second attachment structure. The second attachment structure comprises two engine attachments for recovering the moment along the axis of the engine, laid out on either side of a horizontal symmetry plane of the engine.