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    Method of forming unit having casing and convergent portion
    1.
    发明专利
    Method of forming unit having casing and convergent portion 有权
    成型装置和合并部分的方法

    公开(公告)号：JP2008169830A

    公开(公告)日：2008-07-24

    申请号：JP2007322968

    申请日：2007-12-14

    Applicant: Snecma Propulsion Solide ,  スネクマ・プロピュルシオン・ソリドSnecma Propulsion Solide

    Inventor： LALANDE JOELLE ,  BALLION FREDERIC

    IPC: F02K9/97

    CPC classification number: B29C70/48 ,  B29C70/222 ,  B29C70/226 ,  B29C70/345 ,  B29C70/382 ,  B29C70/462 ,  B29K2033/04 ,  B29K2995/0015 ,  B29K2995/0017 ,  B29K2995/0082 ,  B29K2995/0087 ,  B29L2031/3097 ,  Y10T156/1074

    Abstract: PROBLEM TO BE SOLVED: To provide a method of forming a unit for reducing the number of components and operations required for forming the unit having a casing and a convergent portion. SOLUTION: The method of forming the unit having the casing and the convergent portion comprises steps of: forming a fiber reinforced material 150 from a first fiber preform 50 formed of first type fibers and a second fiber preform 100 formed of second type fibers different from the first type fibers and arranged on the first preform; holding the fiber reinforced material on a tool 200 so that its shape corresponds to the shape of the unit having the casing and the convergent portion; and impregnating the fiber reinforced material with a thermosetting resin 204 to polymerize the resin. COPYRIGHT: (C)2008,JPO&INPIT

    Abstract translation: 要解决的问题：提供一种形成用于形成具有壳体和收敛部分的单元所需的部件数量和操作数量的单元的方法。 解决方案：形成具有壳体和收敛部分的单元的方法包括以下步骤：从由第一类型纤维形成的第一纤维预制件50和由第二类型纤维形成的第二纤维预制件100形成纤维增强材料150 与第一类型的纤维不同，并且布置在第一预成型件上; 将纤维增强材料保持在工具200上，使得其形状对应于具有壳体和收敛部分的单元的形状; 并用热固性树脂204浸渍纤维增强材料以聚合树脂。 版权所有（C）2008，JPO＆INPIT

    System and method controlling pressure oscillation hydrodynamically generated in solid propellant rocket engine
    3.
    发明专利
    System and method controlling pressure oscillation hydrodynamically generated in solid propellant rocket engine 有权
    在固体推进剂发动机中产生的压力振荡的系统和方法

    公开(公告)号：JP2004100706A

    公开(公告)日：2004-04-02

    申请号：JP2003321545

    申请日：2003-09-12

    Applicant: Snecma Propulsion Solide ,  スネクマ・プロピュルシオン・ソリドSnecma Propulsion Solide

    Inventor： LE HELLEY PHILIPPE ,  JACQUES LOUIS ,  MAGNIERE CHRISTOPHE ,  UHRIG GILLES ,  BONDON BERNARD ,  TRICOT JEAN CLAUDE ,  BOURY DIDIER

    IPC: F02K9/34 ,  F02K9/26 ,  F02K9/32

    CPC classification number: F02K9/26 ,  F02K9/32

    Abstract: PROBLEM TO BE SOLVED: To provide a system passively controlling pressure oscillation hydrodynamically generated in a solid propellant rocket engine 61.
    SOLUTION: This solid propellant rocket engine having a body 62 storing a loading material 63 of solid propellant is characterized in having, at least, a single inclusion 100 laterally positioned to the flow direction E of combustion gas of the solid propellant in the body of the rocket engine. The inclusion is provided with an opening part 101 having a non-axisymmetrical shape for producing a three-dimensional effect to the flow and preventing the formation of a turbulent flow mode in the rocket engine. Such a system can be applicable to an existing rocket engine.
    COPYRIGHT: (C)2004,JPO

    Abstract translation: 要解决的问题：提供一种被动地控制在固体推进剂火箭发动机61中流体动力学产生的压力振荡的系统。解决方案：具有存储固体推进剂的装载材料63的主体62的固体推进剂火箭发动机的特征在于 具有至少一个横向地定位在火箭发动机主体中的固体推进剂的燃烧气体的流动方向E的单个夹具100。 该夹杂物设置有具有非轴对称形状的开口部分101，用于产生流动的三维效果并防止在火箭发动机中形成湍流模式。 这样的系统可以适用于现有的火箭发动机。 版权所有（C）2004，JPO

    Heat treatment oven with inductive heating
    6.
    发明专利
    Heat treatment oven with inductive heating 审中-公开
    具有感应加热的热处理炉

    公开(公告)号：JP2010002171A

    公开(公告)日：2010-01-07

    申请号：JP2009102135

    申请日：2009-04-20

    Applicant: Snecma Propulsion Solide ,  スネクマ・プロピュルシオン・ソリドSnecma Propulsion Solide

    Inventor： DELPERIER BERNARD ,  BAUDRY YVAN ,  PETITJEAN OLIVIER

    IPC: F27D11/06 ,  F27B17/00 ,  F27D13/00

    CPC classification number: C23C16/045 ,  C23C16/452

    Abstract: PROBLEM TO BE SOLVED: To provide a heat treatment oven with inductive heating that enables effective preheating without requiring a large volume for a gas heater zone.
    SOLUTION: This heat treatment oven 10 includes a loading or treatment zone 30, at least one gas inlet 22, a gas preheater chamber 50 situated in the heat treatment oven between the gas inlet 22 and the loading or treatment zone 30, a susceptor having at least one sidewall 12 surrounding the preheater chamber 50 and the loading or treatment zone 30, and a field winding 18 suitable for heating the sidewall 12 by electromagnetic induction. The portion 121 of the sidewall 12 of the susceptor that is situated around the preheater chamber 50 has at least two recessed portions 1210 spaced apart circumferentially from one another to form portions of reduced thickness in the portion of the sidewall.
    COPYRIGHT: (C)2010,JPO&INPIT

    Abstract translation: 要解决的问题：提供具有感应加热的热处理烘箱，其能够有效预热，而不需要用于气体加热器区域的大体积。 解决方案：该热处理炉10包括装载或处理区域30，至少一个气体入口22，位于气体入口22和装载或处理区域30之间的热处理炉中的气体预热器室50， 具有围绕预热器室50和装载或处理区域30的至少一个侧壁12的基座以及适于通过电磁感应加热侧壁12的励磁绕组18。 位于预热室50周围的基座的侧壁12的部分121具有至少两个彼此间隔开的凹陷部分1210，以在侧壁部分中形成厚度减小的部分。 版权所有（C）2010，JPO＆INPIT

    Gas turbine combustion chamber made of cmc material and subdivided into sectors
    7.
    发明专利
    Gas turbine combustion chamber made of cmc material and subdivided into sectors 有权
    CMC材料的气体涡轮机燃烧室，分散在部分

    公开(公告)号：JP2009293914A

    公开(公告)日：2009-12-17

    申请号：JP2009090584

    申请日：2009-04-03

    Applicant: Snecma Propulsion Solide ,  スネクマ・プロピュルシオン・ソリドSnecma Propulsion Solide

    Inventor： HABAROU GEORGES ,  CAMY PIERRE ,  CARRERE BENOIT ,  BOUILLON ERIC

    IPC: F23R3/42 ,  F01D11/00 ,  F01D25/00 ,  F02C7/00 ,  F02C7/28 ,  F16J15/10 ,  F23R3/50

    CPC classification number: F23R3/002 ,  F23M2900/05005 ,  F23R3/007 ,  F23R3/50 ,  F23R3/60 ,  F23R2900/00005 ,  F23R2900/00012 ,  F23R2900/00018

    Abstract: PROBLEM TO BE SOLVED: To provide a combustion chamber structure, absorbing a thermal expansion difference between metal and ceramics. SOLUTION: Elastically deformable link parts 17 and 27 of an annular combustion chamber connect the inner wall and the outer wall of a chamber to inner and outer casings 15 and 25 that are made of metal. The assembly formed by the inner wall, the outer wall, and the end wall of the combustion chamber is subdivided circumferentially into adjacent chamber sectors, each sector being made as a single piece of ceramic composite material and comprising an inner wall sector 110, an outer wall sector 120, and a chamber end wall sector 130. The link parts 17 and 27 connect the inner metal casing and the outer metal casing respectively to each inner wall sector of the combustion chamber and to each outer wall sector of the chamber. The chamber end wall sectors are in contact with a one-piece ring 32 to which they are connected. COPYRIGHT: (C)2010,JPO&INPIT

    Abstract translation: 要解决的问题：提供吸收金属和陶瓷之间的热膨胀差的燃烧室结构。 解决方案：环形燃烧室的可弹性变形的连杆部分17和27将腔室的内壁和外壁连接到由金属制成的内壳体和外壳体15和25。 由燃烧室的内壁，外壁和端壁形成的组件沿圆周方向细分成邻近的腔室部分，每个扇区被制成单片陶瓷复合材料，并且包括内壁扇区110，外壁扇区110 壁扇区120和室端壁扇区130.连接部分17和27将内金属壳体和外金属壳体分别连接到燃烧室的每个内壁扇区和室的每个外壁扇区。 腔室端壁扇区与其连接的一体式环32接触。 版权所有（C）2010，JPO＆INPIT

    Gas turbine combustion chamber having inner and outer walls subdivided into sectors
    10.
    发明专利
    Gas turbine combustion chamber having inner and outer walls subdivided into sectors 有权
    内部和外部的气体涡轮燃烧室分为两部分

    公开(公告)号：JP2009293915A

    公开(公告)日：2009-12-17

    申请号：JP2009090586

    申请日：2009-04-03

    Applicant: Snecma Propulsion Solide ,  スネクマ・プロピュルシオン・ソリドSnecma Propulsion Solide

    Inventor： CARRERE BENOIT ,  HABAROU GEORGES ,  SPRIET PATRICK ,  CAMY PIERRE

    IPC: F23R3/42 ,  F01D11/00 ,  F01D25/00 ,  F02C7/28 ,  F16J15/10

    CPC classification number: F23R3/002 ,  F23R3/007 ,  F23R3/50 ,  F23R3/60 ,  F23R2900/00005

    Abstract: PROBLEM TO BE SOLVED: To provide a combustion chamber structure preventing deformation by a thermal expansion difference between metal and ceramics.
    SOLUTION: Elastically deformable link elements 17 and 27 connect an inner wall and an outer chamber wall to inner and outer metal casings. Each of the inner and outer chamber walls 10 and 20 is subdivided circumferentially into adjacent sectors 100 and 200 along longitudinal edges, each sector extending continuously from the end wall to the opposite end of the chamber and being folded outward from the chamber at each of its longitudinal edges to form a portion having a U-shaped cross-section terminated by a folded-back margin 102, 202 that is spaced apart from the outer face of the corresponding chamber wall. The link elements 17 and 27 are connected to the inner and outer chamber walls by being fastened to the sector margins.
    COPYRIGHT: (C)2010,JPO&INPIT

    Abstract translation: 要解决的问题：提供一种防止金属和陶瓷之间的热膨胀差异变形的燃烧室结构。 解决方案：弹性变形的连接元件17和27将内壁和外部室壁连接到内部和外部金属外壳。 内室壁10和外室20的每一个沿着纵向边缘周向地细分成邻近的扇区100和200，每个扇区从端壁连续延伸到室的相对端，并且在室的每一个 纵向边缘以形成具有由折叠边缘102,202终止的U形横截面的部分，该折回边缘102,202与相应的室壁的外表面间隔开。 连杆元件17和27通过紧固到扇形边缘而连接到内室和外室壁。 版权所有（C）2010，JPO＆INPIT

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