公开(公告)号：US20140334913A1

公开(公告)日：2014-11-13

申请号：US14362490

申请日：2012-12-05

Applicant: SNECMA

Inventor： Dominik Igel ,  Delphine Leroux

IPC: F01D11/04

CPC classification number: F01D11/04 ,  F01D11/001 ,  F01D25/183 ,  F02C7/28 ,  F05D2240/55 ,  F05D2240/57 ,  F05D2260/98 ,  F16J15/406 ,  F16J15/42

Abstract: A system for sealing an oil chamber from an adjoining exterior volume, and a turbo-machine including a sealing system. The system for sealing the oil chamber from the adjoining exterior volume, both of which are delimited by a mobile rotor in rotation about an axis and a part, fixed or mobile, includes: a first seal arranged between the rotor and the part; a second seal that is mounted between the rotor and the part and which is offset longitudinally relative to the first seal, to form with the first seal a sealing chamber delimited by the rotor, the part, and the two seals; and a mechanism for supplying gas to the sealing chamber, such that the gas can be compressed when the rotor begins to rotate, the chamber communicating with the oil chamber and/or the adjoining exterior volume via the first and second seals alone, respectively.

Abstract translation: 一种用于从相邻的外部容积密封油室的系统，以及包括密封系统的涡轮机。 用于将密封腔室与毗邻的外部容积密封的系统，两者都由围绕轴线旋转的可移动转子和固定或可移动的部件限定，包括：设置在转子和部件之间的第一密封件; 第二密封件，其安装在所述转子和所述部件之间并相对于所述第一密封件纵向偏移，以与所述第一密封件一起形成由所述转子，所述部件和所述两个密封件限定的密封室; 以及用于向密封室供应气体的机构，使得当转子开始旋转时，气体可以被压缩，腔室分别经由第一和第二密封件与油室和/或相邻的外部容积连通。

公开(公告)号：US09982551B2

公开(公告)日：2018-05-29

申请号：US14362490

申请日：2012-12-05

Applicant: SNECMA

Inventor： Dominik Igel ,  Delphine Leroux

IPC: F01D11/04 ,  F04D29/10 ,  F01D11/00 ,  F01D25/18 ,  F02C7/28 ,  F16J15/42 ,  F16J15/40

CPC classification number: F01D11/04 ,  F01D11/001 ,  F01D25/183 ,  F02C7/28 ,  F05D2240/55 ,  F05D2240/57 ,  F05D2260/98 ,  F16J15/406 ,  F16J15/42

Abstract: A system for sealing an oil chamber from an adjoining exterior volume, and a turbo-machine including a sealing system. The system for sealing the oil chamber from the adjoining exterior volume, both of which are delimited by a mobile rotor in rotation about an axis and a part, fixed or mobile, includes: a first seal arranged between the rotor and the part; a second seal that is mounted between the rotor and the part and which is offset longitudinally relative to the first seal, to form with the first seal a sealing chamber delimited by the rotor, the part, and the two seals; and a mechanism for supplying gas to the sealing chamber, such that the gas can be compressed when the rotor begins to rotate, the chamber communicating with the oil chamber and/or the adjoining exterior volume via the first and second seals alone, respectively.

公开(公告)号：US09879607B2

公开(公告)日：2018-01-30

申请号：US14095072

申请日：2013-12-03

Applicant: SNECMA

Inventor： Antoine Robert Alain Brunet ,  Delphine Leroux ,  Gilles Aouizerate

IPC: F02C7/28 ,  F01D11/02 ,  F01D25/16

CPC classification number: F02C7/28 ,  F01D11/02 ,  F01D25/162 ,  F05D2240/56 ,  Y02T50/671

Abstract: A sealing device for an enclosure of a turbine engine formed by an assembly of juxtaposed rotating and/or static bodies is provided. The sealing device includes at least one brush seal having a brush body, carried by at least one first member, and bristles extending from the brush body and arranged so as to rub against at least one second member rotatable relative to the first member, so as to produce a pressure difference between the inside of said enclosure and its outer environment. The device further includes a labyrinth-type seal, the labyrinth being positioned in series with the brush seal between the inside of the enclosure and its outer environment.

公开(公告)号：US10336464B2

公开(公告)日：2019-07-02

申请号：US15100246

申请日：2014-12-22

Applicant: SNECMA

Inventor： Pierrick Charlemagne ,  Delphine Leroux

IPC: A62C3/08 ,  F02C7/12 ,  F02C7/25 ,  B64C7/02 ,  B64D29/00 ,  B64D45/00 ,  F01D25/24

Abstract: An aircraft propulsion assembly includes an engine, a nacelle surrounding the engine, and a system for extinguishing a fire that may occur in the engine and/or in the nacelle. The extinguishing system has means for supplying an extinguishant to at least one extinguishant distribution pipe which opens into a cavity of the engine and/or a cavity of the nacelle. The extinguishing system also includes means for supplying said at least one pipe with air so as to ventilate the or each cavity.

公开(公告)号：US20160368618A1

公开(公告)日：2016-12-22

申请号：US15100246

申请日：2014-12-22

Applicant: SNECMA

Inventor： Pierrick Charlemagne ,  Delphine Leroux

IPC: B64D45/00 ,  F01D25/24 ,  B64C7/02

CPC classification number: B64D45/00 ,  A62C3/08 ,  B64C7/02 ,  B64D29/00 ,  B64D2045/009 ,  F01D25/24 ,  F02C7/12 ,  F02C7/25 ,  F05D2220/323 ,  Y02T50/675

Abstract: An aircraft propulsion assembly includes an engine, a nacelle surrounding the engine, and a system for extinguishing a fire that may occur in the engine and/or in the nacelle. The extinguishing system has means for supplying an extinguishant to at least one extinguishant distribution pipe which opens into a cavity of the engine and/or a cavity of the nacelle. The extinguishing system also includes means for supplying said at least one pipe with air so as to ventilate the or each cavity.

Abstract translation: 飞机推进组件包括发动机，围绕发动机的机舱和用于熄灭可能在发动机和/或机舱内发生的火的系统。 灭火系统具有将灭火剂供给至少一个通向发动机空腔和/或机舱空腔的灭火剂分配管的装置。 灭火系统还包括用于向所述至少一个管供应空气以使所述或每个空腔通风的装置。