公开(公告)号：US20150377136A1

公开(公告)日：2015-12-31

申请号：US14768748

申请日：2014-02-17

Applicant: SNECMA

Inventor： Francois Robert Bellabal

IPC: F02C7/20 ,  B64D27/26 ,  F02K3/02

CPC classification number: F02C7/20 ,  B64D27/26 ,  F01D25/162 ,  F01D25/28 ,  F02K3/025 ,  F02K3/06 ,  F05D2260/30 ,  Y02T50/44 ,  Y02T50/672

Abstract: Bypass turbojet engine comprising a fan casing (5) at the front and an exhaust casing at the rear, said turbojet engine further comprising a cold stream duct (7) which comprises an annular rear end connected to the exhaust casing and on which is positioned at least one attachment point (4) able to transmit the load from the exhaust casing to the structure of an aircraft, characterized in that a plurality of attachment points (4g, 4d) is positioned on the circumference of said annular rear end of the cold stream duct (7), said plurality of attachment points comprising either two points (4g, 4d) that are diametrically opposed on said circumference or at least three points that form a polygon through which the axis of symmetry of the cold stream duct (7) passes, and in that the turbojet engine is equipped with a rear suspension hoop (8) fixed to said attachment points and able to be fixed to the structure of the aircraft.

Abstract translation: 旁路涡轮喷气发动机包括在前部的风扇壳体（5）和后部的排气壳体，所述涡轮喷气发动机还包括冷流管道（7），其包括连接到排气壳体的环形后端，并在其上定位 至少一个连接点（4），其能够将负载从排气壳体传送到飞行器的结构，其特征在于，多个附接点（4g，4d）位于冷流的所述环形后端的圆周上 所述多个附接点包括在所述圆周上直径相对的两个点（4g，4d）或至少三个点，所述至少三个点形成冷流管（7）的对称轴通过的多边形 并且涡轮喷气发动机配备有固定到所述附接点的后悬挂箍（8），并能够固定在飞行器的结构上。

公开(公告)号：US20160200443A1

公开(公告)日：2016-07-14

申请号：US14914349

申请日：2014-08-21

Applicant: SNECMA

Inventor： Francois Robert Bellabal ,  Francois Gallet ,  Mathieu Ange Poisson

IPC: B64D27/26 ,  B64D27/16 ,  F02K1/04

CPC classification number: F01D25/16 ,  B64D27/16 ,  B64D27/26 ,  B64D2027/266 ,  F02C7/20 ,  F02K1/04 ,  F02K3/06 ,  F05D2220/323 ,  Y02T50/672

Abstract: The invention relates to a bypass turbojet comprising an exhaust housing having a central hub (13) and connecting means (11) that can transmit the forces generated by the turbojet to the structure of the aircraft that it propels, said connection means being two arms extending radially from the central hub in order to cross the cold flow of said turbojet and being characterised in that they are secured to said central hub and positioned in a diametrically opposed manner in relation to each other. An additional connection means (14) extends between the hub (13) and the area (9) for securing the exhaust housing to the structure (12) of the aircraft in order to transmit the exceptional dimensioning loads, said connection means being on standby during normal use, without any transmission of force between said hub and said area.

Abstract translation: 本发明涉及一种旁通涡轮喷气发动机，其包括具有中心轮毂（13）和连接装置（11）的排气壳体，该连接装置可将由涡轮喷气发生的力传递到其所推进的飞行器的结构，所述连接装置是两个臂 径向地从中心轮毂排出以便穿过所述涡轮喷气发动机的冷流，并且其特征在于它们固定到所述中心轮毂并相对于彼此以直径相对的方式定位。 另外的连接装置（14）在轮毂（13）和区域（9）之间延伸，用于将排气罩固定到飞行器的结构（12），以便传递异常尺寸的载荷，所述连接装置在 正常使用，在所述轮毂和所述区域之间没有任何的力传递。

公开(公告)号：US09863273B2

公开(公告)日：2018-01-09

申请号：US14914349

申请日：2014-08-21

Applicant: SNECMA

Inventor： Francois Robert Bellabal ,  Francois Gallet ,  Mathieu Ange Poisson

IPC: F01D25/16 ,  B64D27/16 ,  F02K1/04 ,  B64D27/26 ,  F02K3/06 ,  F02C7/20

CPC classification number: F01D25/16 ,  B64D27/16 ,  B64D27/26 ,  B64D2027/266 ,  F02C7/20 ,  F02K1/04 ,  F02K3/06 ,  F05D2220/323 ,  Y02T50/672

Abstract: The invention relates to a bypass turbojet comprising an exhaust housing having a central hub (13) and connecting means (11) that can transmit the forces generated by the turbojet to the structure of the aircraft that it propels, said connection means being two arms extending radially from the central hub in order to cross the cold flow of said turbojet and being characterized in that they are secured to said central hub and positioned in a diametrically opposed manner in relation to each other. An additional connection means (14) extends between the hub (13) and the area (9) for securing the exhaust housing to the structure (12) of the aircraft in order to transmit the exceptional dimensioning loads, said connection means being on standby during normal use, without any transmission of force between said hub and said area.

公开(公告)号：US20140311161A1

公开(公告)日：2014-10-23

申请号：US14362267

申请日：2012-12-10

Applicant: SNECMA

Inventor： Francois Robert Bellabal ,  Eric De Vulpillieres

IPC: F02C7/20

CPC classification number: F02C7/20 ,  F01D5/145 ,  F01D9/00 ,  F01D25/162 ,  F01D25/28 ,  F02K1/80 ,  F02K3/06 ,  F05D2210/33 ,  F05D2240/31 ,  Y02T50/671 ,  Y02T50/673 ,  Y10T29/49229

Abstract: A method for creating a connecting element, arranged between two components of a structure, or a turbojet engine structure, which is subjected to compressive and/or tensile loadings and which includes a hollow shaft immersed, at least partially, in a stream of air flowing between the two components, the method including: dimensioning a width of the main cross section associated with the shaft of the connecting element in a direction orthogonal to the longitudinal axis of the shaft according to desired mechanical strength and desired mass, and according to characteristics of the airstream; and working an external surface of the shaft of the connecting element, at least over part of this surface, to give it a surface finish with an arithmetic mean roughness at least equal to 20 microns, to reduce drag of the connecting element thus dimensioned by comparison with a smooth connecting element of the same diameter.

Abstract translation: 一种用于产生布置在结构的两个部件之间的连接元件或涡轮喷气发动机结构的方法，所述连接元件经受压缩和/或拉伸载荷，并且包括至少部分地浸没在空气流中的空心轴 在所述两个部件之间，所述方法包括：根据期望的机械强度和所需质量，在与轴的纵向轴线正交的方向上确定与连接元件的轴相关联的主横截面的宽度，并且根据 气流 并且至少在该表面的一部分上加工连接元件的轴的外表面，以使其具有至少等于20微米的算术平均粗糙度的表面光洁度，以减少通过比较确定尺寸的连接元件的阻力 具有相同直径的平滑连接元件。

公开(公告)号：US10184401B2

公开(公告)日：2019-01-22

申请号：US14768748

申请日：2014-02-17

Applicant: SNECMA

Inventor： Francois Robert Bellabal

IPC: F02C7/20 ,  B64D27/26 ,  F01D25/16 ,  F01D25/28 ,  F02K3/06 ,  F02K3/02

Abstract: Bypass turbojet engine comprising a fan casing (5) at the front and an exhaust casing at the rear, said turbojet engine further comprising a cold stream duct (7) which comprises an annular rear end connected to the exhaust casing and on which is positioned at least one attachment point (4) able to transmit the load from the exhaust casing to the structure of an aircraft, characterized in that a plurality of attachment points (4g, 4d) is positioned on the circumference of said annular rear end of the cold stream duct (7), said plurality of attachment points comprising either two points (4g, 4d) that are diametrically opposed on said circumference or at least three points that form a polygon through which the axis of symmetry of the cold stream duct (7) passes, and in that the turbojet engine is equipped with a rear suspension hoop (8) fixed to said attachment points and able to be fixed to the structure of the aircraft.