公开(公告)号：US20170002747A1

公开(公告)日：2017-01-05

申请号：US15104445

申请日：2014-12-15

Applicant: SNECMA

Inventor： Jérémy Edmond Fert ,  Eric De Vulpillieres ,  Julien Pavillet

IPC: F02C9/18 ,  F01D25/30 ,  F01D25/24 ,  F02C7/141 ,  B64D27/10 ,  B64D29/00

CPC classification number: F02C9/18 ,  B64D13/00 ,  B64D15/04 ,  B64D27/10 ,  B64D29/00 ,  B64D2013/0618 ,  F01D25/24 ,  F01D25/30 ,  F02C6/08 ,  F02C7/14 ,  F02C7/141 ,  F05D2220/323 ,  F05D2260/213 ,  Y02T50/672 ,  Y02T50/675

Abstract: The invention relates to an aircraft turbomachine comprising a nacelle and an engine comprising at least one outflowing jet of air, wherein a heat exchanger of the precooler type for supplying air to the aircraft is mounted in the nacelle, said exchanger comprising a primary circuit, the inlet of which is connected to means for taking compressed air from the engine and the outlet of which is connected to means for supplying air to the aircraft, and a secondary circuit supplied with air taken from said air flow.

Abstract translation: 本发明涉及一种包括机舱和发动机的飞机涡轮机，该机舱和发动机包括至少一个流出的空气流，其中用于向飞行器供应空气的预冷器类型的热交换器安装在机舱中，所述交换器包括主回路， 其入口连接到用于从发动机获取压缩空气并且其出口连接到用于向飞行器供应空气的装置的装置以及从所述空气流供应的空气的二次回路。

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：US11060462B2

公开(公告)日：2021-07-13

申请号：US15104445

申请日：2014-12-15

Applicant: SNECMA

Inventor： Jérémy Edmond Fert ,  Eric De Vulpillieres ,  Julien Pavillet

IPC: F02C9/18 ,  F02C7/14 ,  B64D13/00 ,  F02C6/08 ,  B64D27/10 ,  B64D29/00 ,  F01D25/24 ,  F01D25/30 ,  F02C7/141 ,  B64D15/04 ,  B64D13/06

Abstract: An aircraft turbomachine including a nacelle and an engine further including at least one outflowing jet of air, wherein a heat exchanger of the precooler type for supplying air to the aircraft is mounted in the nacelle. The exchanger includes a primary circuit, the inlet of which is connected to a supply of compressed air from the engine and the outlet of which is connected to an air supply for supplying air to the aircraft, and a secondary circuit supplied with air taken from said air flow.