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    Acoustic igniter and ignition method for propellant liquid rocket engine
    1.
    发明申请
    Acoustic igniter and ignition method for propellant liquid rocket engine 有权

    公开(公告)号：US20010001360A1

    公开(公告)日：2001-05-24

    申请号：US09757411

    申请日：2001-01-09

    申请人： SOCIETE NATIONALE D'ETUDE ET DE CONSTRUCTION DE MOTEURS D'AVIATION - S.N.E.C.M.A.

    发明人： Khoze Kessaev ,  Vassili Zinoviev ,  Vladimir Demtchenko

    IPC分类号： B63H011/00

    CPC分类号： F02K9/95

    摘要： The invention concerns an acoustic igniter for igniting a mixture of rocket fuels in a liquid propellant rocket engine combustion chamber comprising a cylindrical precombustion chamber (101) including a cylindrical wall (111) and first and second end walls (112, 113), a rocket fuel injection nozzle (103) emerging into the precombustion chamber (101) through the first end wall (112) via an orifice of diameter dn, a rocket fuel injector (104) arranged inside said nozzle (103) along the axis thereof, at least an outlet orifice (102) of minimum diameter df provided in the cylindrical wall (111), an acoustic resonator (105) defining a cavity opening into the precombustion chamber (101) opposite the nozzle (103), through the second end wall (113), via an orifice (151) of diameter dr. The acoustic resonator (105) is enclosed by a housing (106) which defines around the acoustic resonator (105) a closed auxiliary chamber (160) which communicates only with the precombustion chamber (101) by at least one conduit (107).

    Separator for a two-head combustor chamber
    2.
    发明授权
    Separator for a two-head combustor chamber 失效
    两头燃烧室的分离器

    公开(公告)号：US6155055A

    公开(公告)日：2000-12-05

    申请号：US291276

    申请日：1999-04-14

    申请人： Alexandre Forestier

    发明人： Alexandre Forestier

    IPC分类号： F02C7/18 ,  F23R3/34 ,  F23R3/42 ,  F23R3/16

    CPC分类号： F23R3/34

    摘要： A separator (10) for a two-head combustion chamber which comprises a plurty of segments (11) that are arrayed circumferentially and spaced apart a distance (x) from one another and that are affixed to appropriately shaped sheetmetal (12, 13) of the combustion chamber. Each segment (11) is shaped as an elongated, hollow body with an upper wall (17) and a lower wall (18). The segments are cooled by air from an upstream portion of an end of the combustion chamber entering the segments (11) and exhausting by a plurality of orifices (34) in the segment walls (17, 18). The upper and lower segment walls (17) and (18) are respectively heat-protected by two sets of tiles (40, 41), each of the tiles straddling two adjacent segments, being spaced a distance from the walls (17, 18) to subtend an enclosed space (46, 47) therebetween, and having at least one tile orifice (48, 49, 50) which allows the cooling air from the segments (11) to exhaust into the heads.

    摘要翻译： 一种用于双头燃烧室的分离器（10），其包括多个段（11），所述多个段（11）周向排列并且间隔开彼此的距离（x），并且被固定到适当形状的金属板（12,13）上 燃烧室。 每个段（11）成形为具有上壁（17）和下壁（18）的细长的中空体。 这些段由空气从进入段（11）的燃烧室的端部的上游部分冷却，并且通过段壁（17,18）中的多个孔（34）排出。 上部和下部分段壁（17）和（18）分别由两组瓦片（40,41）分别进行热保护，每个瓦片横跨两个相邻的区段，与墙壁（17,18）隔开一定距离， 以对置其间的封闭空间（46,47），并且具有允许来自段（11）的冷却空气排入头部的至少一个瓦片孔口（48,49,50）。

    Method and device for reversing the thrust of very high bypass ratio turbojet engines
    3.
    发明授权
    Method and device for reversing the thrust of very high bypass ratio turbojet engines 有权
    用于反转非常高的旁路比涡轮喷气发动机的推力的方法和装置

    公开(公告)号：US6148605A

    公开(公告)日：2000-11-21

    申请号：US262345

    申请日：1999-03-04

    申请人： Alain Lardellier

    发明人： Alain Lardellier

    IPC分类号： F01D1/30 ,  F02C3/113 ,  F02C7/36 ,  F16H3/60 ,  F02K3/02

    CPC分类号： F16H3/60 ,  F01D1/30 ,  F02C3/113 ,  F02C7/36 ,  Y02T50/671

    摘要： A high bypass ratio turbojet engine comprising a fan rotated by the shaft of a low pressure turbine via a speed reducer is provided with a thrust reverser device by providing the speed reducer with first and second epicyclic gear trains which are mounted in parallel between the low pressure turbine and the fan and which are arranged in such a way as to drive the fan in a first direction of rotation when the engine is operated in a direct thrust mode, and to drive the fan in the opposite direction of rotation when the engine is to be operated in the reverse thrust mode.

    摘要翻译： 包括通过减速器由低压涡轮机的轴旋转的风扇的高旁通比涡轮喷气发动机设置有推力反向器装置，其通过为减速器提供第一和第二行星齿轮系，第一和第二行星齿轮系平行安装在低压 涡轮机和风扇，并且当发动机以直接推力模式操作时以这样的方式驱动风扇沿第一旋转方向，并且当发动机转向时驱动风扇沿相反的旋转方向 以反向推力模式操作。

    Optical-fiber polarimetric sensor
    4.
    发明授权
    Optical-fiber polarimetric sensor 失效
    光纤极化传感器

    公开(公告)号：US6118539A

    公开(公告)日：2000-09-12

    申请号：US470486

    申请日：1999-12-22

    申请人： Eric Gaumont ,  Michel Clement ,  Ayoub Chakari ,  Patrick Meyrueis

    发明人： Eric Gaumont ,  Michel Clement ,  Ayoub Chakari ,  Patrick Meyrueis

    IPC分类号： G01B11/16 ,  G01D5/34 ,  G01B11/14

    CPC分类号： G01D5/344 ,  G01B11/18

    摘要： An optical-fiber polarimetric sensor for measuring the displacement of an object relative to a frame, the sensor comprising a measurement optical fiber secured, over a fraction of its length, both to a central point of the object and to first and second fixed points of the frame, means disposed at one end of the measurement fiber and serving to emit a light beam of determined polarization into said measurement fiber, means for exerting twist on the measurement fiber so as to modify the polarization of the light beam, and means disposed at another end of the measurement fiber and serving firstly to detect the resulting light beam and secondly to determine the displacement of the object by analyzing the polarization modified in this way, wherein said measurement fiber is stripped, over said fraction of its length, of the covering that imparts mechanical strength thereto, and it is slid into a deformable guide sheath fixed both to the rotary object and also to the frame. Preferably, the deformable guide sheath is made of fine steel, and it may lined with a flexible protective sheath.

    摘要翻译： 一种用于测量物体相对于框架的位移的光纤偏振传感器，所述传感器包括测量光纤，其测量光纤在其长度的一小部分上被固定到物体的中心点，并且固定到第一和第二固定点 所述框架，设置在所述测量光纤的一端并且用于将确定的偏振光发射到所述测量光纤中的装置，用于在所述测量光纤上施加扭曲以修改所述光束的偏振的装置，以及设置在 测量光纤的另一端，首先用于检测所得到的光束，其次通过分析以这种方式修改的偏振来确定物体的位移，其中所述测量光纤在其长度的所述部分上剥离覆盖物 其赋予机械强度，并且滑动到固定在旋转体上的可变形引导护套和框架。 优选地，可变形引导护套由精细钢制成，并且可以衬有柔性护套。

    Turbojet engine combustion chamber with heat protecting lining
    6.
    发明授权
    Turbojet engine combustion chamber with heat protecting lining 失效
    涡轮喷气发动机燃烧室具有防热衬里

    公开(公告)号：US6029455A

    公开(公告)日：2000-02-29

    申请号：US919353

    申请日：1997-08-28

    申请人： Denis Sandelis

    发明人： Denis Sandelis

    IPC分类号： F23R3/00 ,  F02C1/00 ,  F02G3/00 ,  F23R3/06

    CPC分类号： F23R3/002

    摘要： A combustion chamber is disclosed for a turbojet engine in which the combustion chamber has a forward intake, a rear exit and a perforated casing extending between the intake and exit. The combustion chamber also has at least two rows of insulating tiles arrayed on the casing in forward and rear rows with both rows extending circumferentially around the inner surface of the casing bounding the combustion chamber. Each rear tile has a forward edge portion with a sloping wall and each forward tile has a tapered rear edge portion overlapping the forward edge portion with a clearance therebetween such that the tampered rear edge portion and the sloping wall bound a slot opening into the combustion chamber and slanting towards the rear of the combustion chamber to facilitate the formation of an air cooling film on inner surfaces of the tiles. The cooling air passes through the perforated casing, into the space between the casing and the tiles, through the clearance between the tiles and through the slot into the combustion chamber.

    摘要翻译： 公开了一种用于涡轮喷气发动机的燃烧室，其中燃烧室具有前进气口，后出口和在进气口和出口之间延伸的穿孔壳体。 燃烧室还具有排列在前后两排的壳体上的至少两排绝缘砖，两排沿周向围绕着围绕燃烧室的壳体的内表面延伸。 每个后瓦片具有带有倾斜壁的前边缘部分，并且每个前瓦片具有与前边缘部分重叠的锥形后边缘部分，其间具有间隙，使得被篡改的后边缘部分和倾斜壁限定开口进入燃烧室 并且朝向燃烧室的后部倾斜以便于在瓷砖的内表面上形成空气冷却膜。 冷却空气穿过穿孔的壳体，穿过壳体和瓦片之间的空间，穿过瓦片之间的间隙并通过狭槽进入燃烧室。

    Chemical vapor infiltration method with variable infiltration parameters
    7.
    发明授权
    Chemical vapor infiltration method with variable infiltration parameters 失效
    化学气相渗透法具有可变渗透参数

    公开(公告)号：US6001419A

    公开(公告)日：1999-12-14

    申请号：US930743

    申请日：1997-10-06

    申请人： Jean-Luc Leluan ,  Jean-Luc Domblides ,  Bernard Delperier ,  Jacques Thebault ,  Jean-Marie Toussaint

    发明人： Jean-Luc Leluan ,  Jean-Luc Domblides ,  Bernard Delperier ,  Jacques Thebault ,  Jean-Marie Toussaint

    IPC分类号： C04B35/80 ,  C04B35/83 ,  C23C16/52 ,  F16D69/02 ,  C23C16/00

    CPC分类号： F16D69/023 ,  C04B35/806 ,  C04B35/83

    摘要： Between the start and the end of the chemical vapor infiltration process, filtration conditions are modified by causing at least one of the following infiltration parameters to vary: retention time of the gas, pressure, temperature, concentration of precursor in the gas, and concentration of dopant, if any, in the gas; thereby adapting infiltration conditions to changes in the porometry of the substrate in order to control the microstructure of the material deposited within the substrate, in particular in order to conserve a microstructure that is constant.

    摘要翻译： PCT No.PCT / FR96 / 00530 Sec。 371日期：1997年10月6日 102（e）日期1997年10月6日PCT 1996年4月9日PCT PCT。 公开号WO96 / 31447 日期1996年10月10日在化学气相渗透过程的开始和结束之间，通过使至少一个以下渗透参数变化来改变渗透条件：气体的保留时间，压力，温度，前体浓度 气体和气体中掺杂剂的浓度（如果有的话）; 从而使渗透条件适应于衬底的孔隙率的变化，以便控制沉积在衬底内的材料的微结构，特别是为了保持恒定的微结构。

    Tooling using thermostructural composite materials containing carbon for heat treatment and/or thermochemical treatment installations
    8.
    发明授权
    Tooling using thermostructural composite materials containing carbon for heat treatment and/or thermochemical treatment installations 失效
    使用含碳的热结构复合材料进行热处理和/或热化学处理设备的模具

    公开(公告)号：US5996676A

    公开(公告)日：1999-12-07

    申请号：US732274

    申请日：1996-10-29

    申请人： Jean-Pierre Maumus ,  Jacques Thebault

    发明人： Jean-Pierre Maumus ,  Jacques Thebault

    IPC分类号： B22D19/00 ,  B22D19/14 ,  C04B41/45 ,  C04B41/52 ,  C04B41/90 ,  F27D1/00 ,  F27D3/12 ,  F27D5/00 ,  B22D19/02

    CPC分类号： C04B41/4523 ,  C04B41/52 ,  F27D1/0006 ,  Y10T428/12007 ,  Y10T428/23

    摘要： An interposition layer (12) is formed on the outside surface of a part (10) made of thermostructural composite material containing carbon, and a metal case is formed by casting molten metal (22) around the part provided with its interposition layer. The interposition layer has closed porosity and it is proof against the metal of the case, such that shrinkage of the metal during cooling is absorbed by compacting or collapsing the porosity of the interposition layer, thereby preserving the integrity of the metal case, and the interposition layer constitutes a diffusion barrier preventing eutetics forming by contact between the metal of the case and the composite material.

    摘要翻译： PCT No.PCT / FR96 / 00373 Sec。 371日期1996年10月29日第 102（e）日期1996年10月29日PCT 1996年3月8日PCT公布。 出版物WO96 / 27570 日期1996年9月21日在由包含碳的热结构复合材料制成的部分（10）的外表面上形成介入层（12），并且通过将熔融金属（22）围绕设置有金属壳体 插入层 插入层具有封闭的多孔性，并且它抵抗壳体的金属，使得在冷却期间金属的收缩通过压实或塌缩插入层的孔隙而被吸收，从而保持金属壳体的完整性，并且插入 层构成通过壳体的金属与复合材料之间的接触防止形成的扩散阻挡层。