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    METHOD FOR ASSEMBLING END TO END TWO PARTS HAVING DIFFERENT THERMAL EXPANSION COEFFICIENTS AND ASSEMBLY THUS OBTAINED
    1.
    发明申请
    METHOD FOR ASSEMBLING END TO END TWO PARTS HAVING DIFFERENT THERMAL EXPANSION COEFFICIENTS AND ASSEMBLY THUS OBTAINED 审中-公开
    用于组装末端两端的方法，具有不同的热膨胀系数和组装

    公开(公告)号：WO2008139095A3

    公开(公告)日：2009-04-16

    申请号：PCT/FR2008050600

    申请日：2008-04-03

    Applicant: SNECMA PROPULSION SOLIDE ,  CONETE ERIC

    Inventor： CONETE ERIC

    IPC: F01D25/24 ,  F02K1/80

    CPC classification number: F02K1/80 ,  F01D25/243 ,  F01D25/246 ,  F05D2260/30 ,  F05D2300/21 ,  F05D2300/603 ,  F23R3/007 ,  F23R3/60 ,  Y02T50/672 ,  Y10T29/49947

    Abstract: According to the invention, in order to assemble two parts (154, 162) made of materials having different thermal expansion coefficients at their edge portions (154a, 162a) and engaged with each other, the method comprises forming along the thinned edge of one of the parts tabs (170) separated by slots (172) and obtained by cutting or machining the material of the part, and assembling the parts by attaching them (174) to the tabs. The edge portions are mutually engaged in order to be brought into mutual substantially tight contact at the high temperatures achieved during operation. The invention can particularly be used for assembling parts respectively made of a metal and a ceramic-matrix composite material, in particular in an aircraft gas turbine such as the upstream and downstream secondary nozzles.

    Abstract translation: 根据本发明，为了组装由它们的边缘部分（154a，162a）具有不同热膨胀系数的材料制成并且彼此接合的两个部分（154,162），该方法包括沿着一个 所述部件片（170）由槽（172）分隔并通过切割或加工所述部件的材料而获得，并且通过将所述部件（174）附接到所述突片来组装所述部件。 边缘部分相互接合，以便在操作期间实现的高温下彼此基本紧密接触。 本发明可特别用于组装分别由金属和陶瓷基复合材料制成的部件，特别是在诸如上游和下游次级喷嘴的飞机燃气轮机中。

    FLEXIBLE ABUTMENT LINKS FOR ATTACHING A PART MADE OF CMC
    3.
    发明申请
    FLEXIBLE ABUTMENT LINKS FOR ATTACHING A PART MADE OF CMC 审中-公开
    用于连接由CMC制成的一部分的灵活的分支链接

    公开(公告)号：WO2010026354A4

    公开(公告)日：2010-07-15

    申请号：PCT/FR2009051684

    申请日：2009-09-08

    Applicant: SNECMA PROPULSION SOLIDE ,  CONETE ERIC

    Inventor： CONETE ERIC

    IPC: F02K1/04 ,  F02K1/80

    CPC classification number: F02K1/80 ,  F02K1/04 ,  F05D2230/642

    Abstract: The invention relates to an afterbody assembly for an aeronautical engine including an annular part (60), made of metal material and rigidly connected to the aeronautical engine, and to an afterbody part (20), made of ceramic matrix composite material, the afterbody part (20) being mounted onto the annular part (60) by resiliently flexible mounting lugs (70) and having a first end (71) attached onto the annular part (60) and a second end (72) attached onto the upstream portion of the afterbody part (20). Each mounting lug (70) includes an axial abutment element (720) radially extending from the second end (72) of the lug and at least partially facing the first end (71). The mounting lug (70) also includes a radial abutment element (721) on the second end (72) of the lug, the radial abutment element (721) being at least partially above the first end (71).

    Abstract translation: 用于航空发动机的后体组件技术领域本发明涉及一种用于航空发动机的后体组件，该后体组件包括由金属材料制成并刚性连接到航空发动机的环形部分（60）和由陶瓷基复合材料制成的后体部分（20），后体部分 （20）通过弹性柔性安装凸耳（70）安装到所述环形部件（60）上并且具有附接到所述环形部件（60）上的第一端部（71）和附接到所述环形部件（60）的所述上游部件 后体部分（20）。 每个安装凸耳（70）包括从凸耳的第二端部（72）径向延伸并且至少部分地面向第一端部（71）的轴向抵接元件（720）。 安装凸耳（70）还包括在凸耳的第二端（72）上的径向邻接元件（721），径向邻接元件（721）至少部分地在第一端（71）之上。

    FLEXIBLE ABUTMENT LINKS FOR ATTACHING A PART MADE OF CMC
    4.
    发明申请
    FLEXIBLE ABUTMENT LINKS FOR ATTACHING A PART MADE OF CMC 审中-公开

    公开(公告)号：WO2010026354A2

    公开(公告)日：2010-03-11

    申请号：PCT/FR2009051684

    申请日：2009-09-08

    Applicant: SNECMA PROPULSION SOLIDE ,  CONETE ERIC

    Inventor： CONETE ERIC

    IPC: F02K1/04 ,  F02K1/80

    CPC classification number: F02K1/80 ,  F02K1/04 ,  F05D2230/642

    Abstract: The invention relates to an afterbody assembly for an aeronautical engine including an annular part (60), made of metal material and rigidly connected to the aeronautical engine, and to an afterbody part (20), made of ceramic matrix composite material, the afterbody part (20) being mounted onto the annular part (60) by resiliently flexible mounting lugs (70) and having a first end (71) attached onto the annular part (60) and a second end (72) attached onto the upstream portion of the afterbody part (20). Each mounting lug (70) includes an axial abutment element (720) radially extending from the second end (72) of the lug and at least partially facing the first end (71). The mounting lug (70) also includes a radial abutment element (721) on the second end (72) of the lug, the radial abutment element (721) being at least partially above the first end (71).

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