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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
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.
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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
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。
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Patent Agency Ranking
3.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：US10428733B2
公开(公告)日：2019-10-01
申请号：US15029588
申请日：2014-10-14
Applicant: SNECMA , SOCIETE LORRAINE DE CONSTRUCTION AERONAUTIQUE
Inventor： Mathieu Ange Poisson , Stéphane Orcel , Guillaume Glemarec , Jean-Luc Pacary
Abstract: A turboprop includes a rotary propeller upstream from an engine and an air intake that is not coaxial to the propeller, said air intake defining a conduit for supplying air to the engine and further defining a bypass to said conduit, the bypass having an outlet oriented substantially axially towards the downstream of the engine. The turboprop further includes a nacelle surrounding the engine and the air intake, wherein the air intake is secured to a housing of the engine and is not rigidly connected to the nacelle, so as to allow, during operation, relative movements between the air intake and the nacelle. The outlet is connected by a flexible link to an intake of an air circuit carried by the nacelle.
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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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公开(公告)号：US09738392B2
公开(公告)日：2017-08-22
申请号：US14762281
申请日：2014-01-15
Applicant: SNECMA
Inventor： Antoine Hellegouarch , Mathieu Ange Poisson , Francois Gallet
CPC classification number: B64D27/26 , B64D27/10 , B64D27/12 , B64D27/14 , F02C7/20 , F02C7/36 , F05D2260/4031
Abstract: A variable geometry suspension structure for suspending a turboprop from a structural element of an aircraft, the structure including a rear cradle for fastening to a structural element of an aircraft and a front cradle for supporting a front portion of the turboprop, the front cradle being connected to the rear cradle, firstly via a pivot connection configured to enable the front cradle to tilt vertically relative to the rear cradle, and secondly by a return spring configured to prevent the front cradle from tilting while thrust from the turboprop is below a predetermined threshold.
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公开(公告)号：US20160237898A1
公开(公告)日：2016-08-18
申请号：US15029588
申请日：2014-10-14
Applicant: SNECMA , SOCIETE LORRAINE DE CONSTRUCTION AERONAUTIQUE
Inventor： Mathieu Ange Poisson , Stéphane Orcel , Guillaume Glemarec , Jean-Luc Pacary
CPC classification number: F02C7/045 , B64D33/02 , B64D2033/0293 , F01D25/243 , F02C7/04 , F02K3/06 , F05D2220/324 , F05D2220/36 , F05D2250/51 , F05D2260/606 , F05D2260/96 , Y02T50/672
Abstract: A turboprop includes a rotary propeller upstream from an engine and an air intake that is not coaxial to the propeller, said air intake defining a conduit for supplying air to the engine and further defining a bypass to said conduit, the bypass having an outlet oriented substantially axially towards the downstream of the engine. The turboprop further includes a nacelle surrounding the engine and the air intake, wherein the air intake is secured to a housing of the engine and is not rigidly connected to the nacelle, so as to allow, during operation, relative movements between the air intake and the nacelle. The outlet is connected by a flexible link to an intake of an air circuit carried by the nacelle.
Abstract translation: 涡轮螺旋桨飞机包括从发动机上游的旋转螺旋桨和不与螺旋桨同轴的进气口，所述进气口限定用于向发动机供应空气并进一步限定到所述导管的旁路的导管，所述旁路具有基本上定向的出口 轴向朝向发动机的下游。 涡轮螺旋桨飞机还包括围绕发动机和进气口的机舱，其中进气口固定到发动机的壳体上，并且不刚性地连接到机舱，以便在运行期间允许进气口和 机舱。 出口通过柔性连杆连接到由机舱承载的空气回路的入口。
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