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1.发明申请GAS TURBINE ENGINE COMPRISING AN EXHAUST CONE ATTACHED TO THE EXHAUST CASING 有权气体涡轮发动机，包括排放在排气管上的排气公开(公告)号：US20150152788A1
公开(公告)日：2015-06-04
申请号：US14403305
申请日：2013-06-20
Applicant: SNECMA
Inventor： Mario Cesar De Sousa , Baghdad Achbari , Benoit Argemiro Matthieu Debray , Sylvain Pichon , Gregory Ghosarossian-Prillieux , Frederic Noel , Nicolas Pommier , Mathieu Ange Poisson
CPC classification number: F02C7/32 , F01D25/24 , F01D25/30 , F02K1/04 , F02K1/80 , F05D2220/32 , F05D2230/60 , F05D2240/91
Abstract: An assembly including an exhaust casing and an exhaust cone for a gas turbine engine, each including an axial annular flange, the two flanges being inserted into one another, one being radially external and the other radially internal, and held together by a mechanical attachment, and the assembly further including a guide by which, during operation of assembling the annular flanges to each other, the exhaust cone is in a predetermined angular position relative to the exhaust casing.
Abstract translation: 一种包括用于燃气涡轮发动机的排气罩和排气锥的组件，每个包括轴向环形凸缘，两个凸缘彼此插入，一个在径向外部，另一个径向内部，并通过机械附件保持在一起， 并且所述组件还包括引导件，通过所述引导件，在将所述环形凸缘彼此组装的操作期间，所述排气锥体相对于所述排气外壳处于预定的角度位置。
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公开(公告)号：US20160131077A1
公开(公告)日：2016-05-12
申请号：US14931604
申请日：2015-11-03
Applicant: SNECMA
Inventor： Benoit Argemiro Matthieu Debray , Mario Cesar De Sousa , Gregory Ghosarossian-Prillieux , Frederic Noel
CPC classification number: F02K1/40 , F01D25/243 , F02K1/386 , F02K1/48 , F02K3/04 , F02K3/06 , F05D2230/232 , F05D2250/311 , F05D2260/941 , Y02T50/671
Abstract: The invention relates to a fairing (37) for a mixer (28) of a nozzle (26) of a dual-flow turbomachine (20), said mixer being of an overall annular shape and extending along a longitudinal axis (24) of the turbomachine, said mixer comprising an upstream part (29) provided with a flange (31) extending radially toward the outside of the mixer, intended to be fastened to an exhaust casing (21) of the turbomachine, and a downstream part (33) forming a flow mixing area, the fairing (37) being of an overall annular shape and configured to extend around the upstream part (29) of the mixer (28) and to be attached to the flange (31) of said upstream part (29), the fairing being without means for fastening to the downstream part (33) of the mixer (28), in such a way as to connect the fairing (37) to the mixer (28) at a distance from the flow mixing area.
Abstract translation: 本发明涉及一种用于双流涡轮机（20）的喷嘴（26）的混合器（28）的整流罩（37），所述混合器具有整体环形形状，并且沿着纵向轴线（24）延伸 涡轮机，所述混合器包括设置有朝向混合器外部径向延伸的凸缘（31）的上游部分（29），用于紧固到涡轮机的排气外壳（21），以及形成 流动混合区域，整流罩（37）为整体环形，并且构造成围绕混合器（28）的上游部分（29）延伸并附接到所述上游部分（29）的凸缘（31） 整流罩没有用于紧固到混合器（28）的下游部分（33）的方式，以便将整流罩（37）连接到距离混合区域一定距离的混合器（28）。
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公开(公告)号：US10273904B2
公开(公告)日：2019-04-30
申请号：US14931604
申请日：2015-11-03
Applicant: SNECMA
Inventor： Benoit Argemiro Matthieu Debray , Mario Cesar De Sousa , Gregory Ghosarossian-Prillieux , Frederic Noel
Abstract: The invention relates to a fairing (37) for a mixer (28) of a nozzle (26) of a dual-flow turbomachine (20), said mixer being of an overall annular shape and extending along a longitudinal axis (24) of the turbomachine, said mixer comprising an upstream part (29) provided with a flange (31) extending radially toward the outside of the mixer, intended to be fastened to an exhaust casing (21) of the turbomachine, and a downstream part (33) forming a flow mixing area, the fairing (37) being of an overall annular shape and configured to extend around the upstream part (29) of the mixer (28) and to be attached to the flange (31) of said upstream part (29), the fairing being without means for fastening to the downstream part (33) of the mixer (28), in such a way as to connect the fairing (37) to the mixer (28) at a distance from the flow mixing area.
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Patent Agency Ranking
公开(公告)号：US09951650B2
公开(公告)日：2018-04-24
申请号：US14547525
申请日：2014-11-19
Applicant: SNECMA
Inventor： Frederic Noel , Benoit Argemiro Matthieu Debray , Mario Cesar De Sousa , Gregory Ghosarossian-Prillieux , Nicolas Pommier
CPC classification number: F01D25/162 , F01D25/18 , F02C7/06 , F05D2220/323 , F05D2230/232 , F05D2240/50 , F16C33/76 , F16C35/045 , F16C35/067
Abstract: The invention relates to a turbomachine bearing support (1) supporting at least one bearing and extending according to a longitudinal principal axis of the turbomachine and comprising: a truncated part (11) having a diameter increasing from upstream to downstream; a flange part (12) which extends from the truncated part (11) as far as the bearing (5, 6) to which it is fixed by an axial flange (121), and having at its downstream end a radial internal flange (17) fixed to an oil inlet cover defining with the bearing (5, 6) an oil inlet container (170); oiled air clearance ducts (71) projecting downstream relative to the flange part (12) and on the oil inlet container (170) and to the other side upstream of the flange part (12) directly radially externally relative to the axial flange (121).
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公开(公告)号：US09932857B2
公开(公告)日：2018-04-03
申请号：US15037642
申请日：2014-11-18
Applicant: SNECMA
Inventor： Frederic Noel , Benoit Argemiro Matthieu Debray , Mario Cesar De Sousa , Gregory Ghosarossian-Prillieux , Nicolas Pommier
CPC classification number: F01D25/162 , F01D25/18 , F02C7/06 , F05D2220/323 , F05D2230/232 , F05D2240/50 , F16C33/76 , F16C35/045 , F16C35/067
Abstract: A bypass engine bearing holder (1) that holds an upstream bearing (6) and defines, with said upstream bearing, an oil chamber (100) and an air chamber (200), comprising a frusto-conical portion (11) defining an upstream bearing chamber (160) and a downstream inner chamber (150), and includes an outer collar (13) connected, by a weld (135), to a flange (15) that extends outward from the frusto-conical portion (11). The outer collar (13) has a sealable gimlet (131) engaging with the upstream bearing (6) such as to seal the oil chamber (100). The bearing holder (1) includes a plurality of oil recovery ducts (8) leading to the downstream inner chamber (150) and to the upstream bearing chamber (160). The oil recovery ducts (8) lead to the upstream bearing chamber (160), downstream from the weld (135) of the outer collar (13) on the flange (15), the weld (135) of the outer collar (13) being axisymmetric.
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公开(公告)号：US09771831B2
公开(公告)日：2017-09-26
申请号：US14494905
申请日：2014-09-24
Applicant: SNECMA
Inventor： Frederic Noel , Benoit Argemiro Matthieu Debray , Mario Cesar De Sousa , Gregory Ghosarossian-Prillieux
CPC classification number: F01D25/30 , F01D25/002 , F01D25/18 , F02C7/06 , F05D2260/602 , F05D2260/607
Abstract: The invention relates to a turbine engine exhaust casing (1), characterized in that it comprises: a hub (2), an outer ring (3); a plurality of structural arms (10) arranged circumferentially between the hub (2) and the outer ring (3); a stiffener (11) extending along at least a portion of the inner circumference of the hub (2), the hub (2) comprising at least one discharge hole (15), and the stiffener (11) comprising at least one discharge slot (16), so as to enable the discharge of a fluid from the casing (1). The invention also relates to a turbine engine comprising such an exhaust casing.
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公开(公告)号：US10006307B2
公开(公告)日：2018-06-26
申请号：US14903266
申请日：2014-07-07
Applicant: SNECMA
Inventor： Benoit Debray , Gregory Ghosarossian-Prillieux , Mario De Sousa , Nicolas Pommier , Frederic Noel
CPC classification number: F01D25/243 , F01D9/02 , F01D25/162 , F01D25/30 , F02C7/20 , F02K1/04 , F05D2220/323 , F05D2230/10
Abstract: The present invention relates to a turbine engine casing (1), in particular a turbojet exhaust casing, including at least one hoop (2) and at least one flange (3, 4) at least partially defining one end of said hoop (2), and at least one cap (5) positioned at least partially on the outer surface of the hoop (2), said cap (5) including a bore (6) capable of receiving an element for fastening the casing (1) to a bracket, the flange including an access cut-out (7a) substantially coaxial with the bore (6) of said at least one cap (5), said access cut-out (7a) enabling access to the bore (6), the access cut-out (7a) being provided at a release cut-out (7b) which is wider than the flange (3, 4) and constitutes a recess on said release cut-out (7b). The invention also relates to a turbine engine including a casing (1) and to a method for machining the latter according to the present invention.
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公开(公告)号：US09897011B2
公开(公告)日：2018-02-20
申请号：US14403305
申请日：2013-06-20
Applicant: SNECMA
Inventor： Mario Cesar De Sousa , Baghdad Achbari , Benoit Argemiro Matthieu Debray , Sylvain Pichon , Gregory Ghosarossian-Prillieux , Frederic Noel , Nicolas Pommier , Mathieu Ange Poisson
CPC classification number: F02C7/32 , F01D25/24 , F01D25/30 , F02K1/04 , F02K1/80 , F05D2220/32 , F05D2230/60 , F05D2240/91
Abstract: An assembly including an exhaust casing and an exhaust cone for a gas turbine engine, each including an axial annular flange, the two flanges being inserted into one another, one being radially external and the other radially internal, and held together by a mechanical attachment, and the assembly further including a guide by which, during operation of assembling the annular flanges to each other, the exhaust cone is in a predetermined angular position relative to the exhaust casing.
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