公开(公告)号：US09217391B2

公开(公告)日：2015-12-22

申请号：US13654796

申请日：2012-10-18

Applicant: SNECMA

Inventor： Francois Gallet ,  Audrey Grede

IPC: F02K3/062 ,  F02K3/072

CPC classification number: F02K3/072 ,  F02K3/062 ,  F05D2220/324 ,  F05D2220/325 ,  Y02T50/672

Abstract: An open rotor type aircraft turbine engine including a contrarotating propeller receiver and a dual-body gas generator having a low-pressure compressor and a high-pressure compressor separated by an intermediate housing, in which the gas generator is arranged upstream from the receiver is provided. The turbine engine includes a structural casing for supporting the receiver, surrounding the gas generator and having a downstream end attached to the receiver and an upstream end attached to the intermediate housing; and a connection device between the structural supporting casing and the gas generator, arranged between the upstream and downstream ends of the casing.

Abstract translation: 提供一种开式转子式飞机涡轮发动机，其包括对转螺旋桨接收器和具有低压压缩机和由其中气体发生器布置在接收器上游的中间壳体分隔的高压压缩机的双体气体发生器 。 涡轮发动机包括用于支撑接收器的结构壳体，围绕气体发生器并且具有附接到接收器的下游端和附接到中间壳体的上游端; 以及布置在壳体的上游和下游端之间的结构支撑壳体和气体发生器之间的连接装置。

公开(公告)号：US20130098066A1

公开(公告)日：2013-04-25

申请号：US13654796

申请日：2012-10-18

Applicant: SNECMA

Inventor： Francois Gallet ,  Audrey Grede

IPC: F02C7/20

CPC classification number: F02K3/072 ,  F02K3/062 ,  F05D2220/324 ,  F05D2220/325 ,  Y02T50/672

Abstract: The present invention relates to an open rotor type aircraft turbine engine (1), comprising a contrarotating propeller receiver (30) and a dual-body gas generator (14) comprising a low-pressure compressor (16) and a high-pressure compressor (18) separated by an intermediate housing (27), said gas generator being arranged upstream from said receiver.According to the invention, the turbine engine further comprises a structural casing (50) for supporting the receiver (30), surrounding the gas generator (14) and having a downstream end (50a) attached to said receiver and an upstream end (50b) attached to said intermediate housing (27). Furthermore, it comprises additional connection means (60) between said structural supporting casing and the gas generator, arranged between the upstream and downstream ends (50b, 50a) of the casing.

Abstract translation: 本发明涉及一种开式转子式飞机涡轮发动机（1），包括对转螺旋桨式接收器（30）和双体气体发生器（14），该双体气体发生器包括低压压缩机（16）和高压压缩机 18），由中间壳体（27）分开，所述气体发生器布置在所述接收器的上游。 根据本发明，涡轮发动机还包括用于支撑接收器（30）的结构壳体（50），围绕气体发生器（14）并且具有附接到所述接收器的下游端（50a）和上游端（50b） 附接到所述中间壳体（27）。 此外，它包括设置在壳体的上游端和下游端（50b，50a）之间的在所述结构支撑壳体和气体发生器之间的附加连接装置（60）。