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    Fixing arrangement for a thermal protection tile in a combustion chamber
    1.
    发明授权
    Fixing arrangement for a thermal protection tile in a combustion chamber 失效
    燃烧室内热保护砖的固定装置

    公开(公告)号：US5560197A

    公开(公告)日：1996-10-01

    申请号：US533277

    申请日：1995-09-25

    Applicant: Denis R. H. Ansart ,  Didier Hernandez ,  Rodolphe Martinez

    Inventor： Denis R. H. Ansart ,  Didier Hernandez ,  Rodolphe Martinez

    IPC: F02K1/82 ,  F16B5/06 ,  F23R3/00 ,  F02C3/14 ,  F02C7/20

    CPC classification number: F16B5/065 ,  F02K1/822 ,  F23R3/002 ,  Y02T50/675

    Abstract: An arrangement for removably fixing a thermal protection tile on the inside of a combustion chamber wall is described. In one form the tile is provided with a fixing stud which is arranged to pass through a hole in the wall, and a split washer is inserted under the head of the stud to lock the assembly to the wall. In another form the tile is provided with a fixing stud having a head which is arranged to be inserted in a socket welded to the inner surface of the wall and which is locked in place by a stop inserted through a hole in the wall to abut the edge of the head and prevent its removal from the socket.

    Abstract translation: 描述了用于可拆卸地将热保护砖固定在燃烧室壁的内部的装置。 在一种形式中，瓦片设置有固定螺柱，其被布置成穿过壁中的孔，并且分离式垫圈插入在螺柱的头部下方以将组件锁定到壁上。 在另一种形式中，瓦片设置有固定螺柱，其具有头部，该头部被布置成插入到焊接到壁的内表面的插座中，并且通过插入壁中的孔的止动件锁定在适当的位置， 头部边缘，防止从插座上拆下。

    Control mechanism for injector diaphragms
    3.
    发明授权
    Control mechanism for injector diaphragms 失效
    喷油器隔膜的控制机构

    公开(公告)号：US4825641A

    公开(公告)日：1989-05-02

    申请号：US69103

    申请日：1987-07-02

    Applicant: Gerard M. F. Mandet ,  Rodolphe Martinez

    Inventor： Gerard M. F. Mandet ,  Rodolphe Martinez

    IPC: F23R3/26 ,  F23R3/50 ,  F02C9/00 ,  F02C1/00

    CPC classification number: F23R3/26 ,  F23R3/50 ,  F05B2250/411

    Abstract: A control mechanism for injector diaphragms in a turbojet engine is disclosed wherein an annular fairing is utilized to synchronize the movement of the individual air-fuel injector diaphragms. The fairing member is interconnected to each of the diaphragms and a single control element controls the rotational movement of the annular fairing. This minimizes the turbulence of the air flow passing around the control system.

    Abstract translation: 公开了一种用于涡轮喷气发动机中的喷射器隔膜的控制机构，其中使用环形整流罩来同步各个空气 - 燃料喷射器隔膜的运动。 整流罩构件互连到每个隔膜，单个控制元件控制环形整流罩的旋转运动。 这样可以最大限度地减少通过控制系统的气流的紊流。

    Fuel and air injection system for a turbojet engine
    4.
    发明授权
    Fuel and air injection system for a turbojet engine 失效
    涡轮喷气发动机的燃油和空气喷射系统

    公开(公告)号：US4696157A

    公开(公告)日：1987-09-29

    申请号：US919126

    申请日：1986-10-15

    Applicant: Gerard Y. G. Barbier ,  Gerald J. P. B. Leboure ,  Michel A. A. Desaulty ,  Rodolphe Martinez ,  Jerome Perigne

    Inventor： Gerard Y. G. Barbier ,  Gerald J. P. B. Leboure ,  Michel A. A. Desaulty ,  Rodolphe Martinez ,  Jerome Perigne

    IPC: F23R3/28 ,  F23C7/00 ,  F23D11/12 ,  F23R3/10 ,  F23R3/26 ,  F23R3/50 ,  F02C3/14

    CPC classification number: F23R3/26 ,  F23C7/008 ,  F23R3/10

    Abstract: A fuel and air injection system for a turbojet engine is disclosed wherein a bowl-shaped member surrounding the fuel injection nozzle defines an impact cooling chamber divided into four sectors. A pair of diametrically opposite sectors have openings to permit air to pass through the cooling chamber into the combustion chamber, while opposite diametrically opposed sectors have openings of larger diameter which also allow communication between the cooling chamber and the combustion chamber. A diaphragm control system allows the air passing into the sectors having the larger diameter openings to be modulated depending upon the throttle setting of the turbojet engine.

    Abstract translation: 公开了一种用于涡轮喷气发动机的燃料和空气喷射系统，其中包围燃料喷射喷嘴的碗状部件限定了被分成四个扇区的冲击冷却室。 一对直径相对的扇区具有允许空气通过冷却室进入燃烧室的开口，而相对的直径相对的扇区具有较大直径的开口，其还允许冷却室和燃烧室之间的连通。 隔膜控制系统允许根据涡轮喷气发动机的节气门设置来调节进入具有较大直径开口的扇区的空气。

    Turbojet engine combustion chamber with a double wall converging zone
    5.
    发明授权
    Turbojet engine combustion chamber with a double wall converging zone 失效
    涡轮喷气发动机燃烧室具有双壁会聚区域

    公开(公告)号：US4901522A

    公开(公告)日：1990-02-20

    申请号：US281749

    申请日：1988-12-09

    Applicant: Patrice Commaret ,  Michel A. A. Desaulty ,  Didier H. Hernandez ,  Jean-Claude Laugeois ,  Gerard M. F. Mandet ,  Rodolphe Martinez

    Inventor： Patrice Commaret ,  Michel A. A. Desaulty ,  Didier H. Hernandez ,  Jean-Claude Laugeois ,  Gerard M. F. Mandet ,  Rodolphe Martinez

    IPC: F23R3/00 ,  F23R3/08

    CPC classification number: F23R3/08 ,  F23R3/002 ,  F05B2260/201 ,  F05B2260/202 ,  Y02T50/675

    Abstract: The combustion chamber according to the present invention utilizes a double-walled structure only in the converging portion of the combustion chamber. A hot wall is retained adjacent to, but spaced from a corresponding cold wall so as to provide a cooling space between them. An upstream portion of the hot wall is retained in a notch defined by the cold wall, while the downstream portions each have generally radially extending flanges. Studs pass through openings in the adjacent flanges to prevent any relative circumferential movement, while a clamp serves to attach the flanges to the inlet of a turbine. The clamp slidably retains the flanges therein so as to permit relative radial movement to accommodate any thermal expansion and contraction of the combustion chamber, solely by the appended claims.

    Abstract translation: 根据本发明的燃烧室仅在燃烧室的会聚部分中使用双壁结构。 热壁与相应的冷壁相邻但间隔开，以便在它们之间提供冷却空间。 热壁的上游部分保持在由冷壁限定的凹口中，而下游部分各自具有大致径向延伸的凸缘。 螺柱穿过相邻凸缘中的开口以防止任何相对的周向运动，而夹具用于将凸缘附接到涡轮机的入口。 夹具可滑动地将凸缘保持在其中，以便仅通过所附权利要求来允许相对径向移动以适应燃烧室的任何热膨胀和收缩。

    Air-fuel injection system for a turbojet engine
    8.
    发明授权
    Air-fuel injection system for a turbojet engine 失效
    涡轮喷气发动机的空气燃料喷射系统

    公开(公告)号：US4809512A

    公开(公告)日：1989-03-07

    申请号：US79149

    申请日：1987-07-29

    Applicant: Gerard Y. G. Barbier ,  Gerard J. P. Bayle-Laboure ,  Michael A. A. Desaulty ,  Rodolphe Martinez ,  Jerome Perigne

    Inventor： Gerard Y. G. Barbier ,  Gerard J. P. Bayle-Laboure ,  Michael A. A. Desaulty ,  Rodolphe Martinez ,  Jerome Perigne

    IPC: F23R3/26 ,  F02C1/00

    CPC classification number: F23R3/26 ,  F05B2250/411

    Abstract: An improved swirler system for a turbojet engine combustion chamber is disclosed in which stationary first vanes and moveable second vanes are oriented at different angles with respect to a radius of the fuel injector system. The different angles allow the angle of the incoming air to be adjusted between full power and idle conditions so as to vary the conial shape of the atomized air-fuel mixture according to the operating conditions of the engine. Radial and axial inlet duct portions serve to attenuate the wakes of the air flow generated by the vanes prior to the air passing into the combustion chamber.

    Abstract translation: 公开了一种用于涡轮喷气发动机燃烧室的改进的旋流器系统，其中固定的第一叶片和可移动的第二叶片相对于燃料喷射器系统的半径以不同的角度定向。 不同的角度允许进入空气的角度在全功率和空转条件之间调节，以便根据发动机的操作条件来改变雾化空气 - 燃料混合物的圆锥形状。 径向和轴向入口管道部分用于在空气进入燃烧室之前衰减由叶片产生的空气流的唤醒。

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