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    Air-fuel injection system for a turbojet engine
    3.
    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

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

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

    IPC分类号： F23R3/26 ,  F02C1/00

    CPC分类号： F23R3/26 ,  F05B2250/411

    摘要： 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.

    摘要翻译： 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。

    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

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

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

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

    CPC分类号： F23R3/26 ,  F23C7/008 ,  F23R3/10

    摘要： 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.

    摘要翻译： 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。

    Low pollution combustion chamber for a turbojet engine
    5.
    发明授权
    Low pollution combustion chamber for a turbojet engine 失效
    用于涡轮喷气发动机的低污染燃烧室

    公开(公告)号：US5295354A

    公开(公告)日：1994-03-22

    申请号：US834820

    申请日：1992-02-13

    申请人： Gerard Y. G. Barbier ,  Xavier, M. H. Bardey ,  Michel A. A. Desaulty ,  Serge M. Meunier

    发明人： Gerard Y. G. Barbier ,  Xavier, M. H. Bardey ,  Michel A. A. Desaulty ,  Serge M. Meunier

    IPC分类号： F23R3/04 ,  F23R3/34 ,  F23R3/42 ,  F23R3/54 ,  F02C3/14

    CPC分类号： F23R3/34 ,  F23R3/04 ,  F23R3/54 ,  Y02T50/675

    摘要： A low pollution combustion chamber for a turbojet engine is disclosed in which first and second combustion chambers are oriented in a counter-flow direction and both combustion chambers communicate with a separate and distinct exhaust chamber. The first combustion chamber has a fuel injector, as well as a primary oxidizer intake, and the wall bounding the first combustion chamber defines a plurality of dilution oxidizer intake orifices. The wall also defines a first exhaust orifice located approximately midway between the upstream and downstream ends of the first combustion chamber. A second combustion chamber has a second fuel injector, as well as a second primary oxidizer intake, but the wall defining the second combustion chamber does not define any dilution oxidizer intake orifices. A second exhaust orifice also communicates with the exhaust chamber. The orientations of the first and second combustion chambers are such that the fuel/oxidizer mixtures traveling through the combustion chambers travel in a generally counterflow arrangement. A separate exhaust chamber is included in the combustion chamber assembly and communicates with the first and second combustion chambers such that the burned gases from these chambers enter the exhaust chamber. The exhaust chamber defines a third exhaust orifice through which the burned gases exit the combustion chamber assembly. The exhaust chamber is oriented such that the exhaust gases passing through this exhaust chamber travel in a direction generally parallel to the gases traveling through the second combustion chamber. A wall defining the combustion chamber defines a second plurality of dilution oxidizer intake orifices so that oxidizer may dilute the exhaust gases passing through this chamber.

    摘要翻译： 公开了一种用于涡轮喷气发动机的低污染燃烧室，其中第一和第二燃烧室在逆流方向上定向，并且两个燃烧室与单独且不同的排气室连通。 第一燃烧室具有燃料喷射器以及初级氧化剂入口，并且与第一燃烧室相邻的壁限定多个稀释氧化剂吸入口。 壁还限定位于第一燃烧室的上游和下游端之间大约中间的第一排气孔。 第二燃烧室具有第二燃料喷射器以及第二主要氧化剂入口，但限定第二燃烧室的壁不限定任何稀释氧化剂吸入口。 第二排气口还与排气室连通。 第一和第二燃烧室的取向使得通过燃烧室运行的燃料/氧化剂混合物以大致逆流排列行进。 在燃烧室组件中包括单独的排气室，并与第一和第二燃烧室连通，使得来自这些室的燃烧气体进入排气室。 排气室限定第三排气孔，燃烧的气体通过该第三排气孔离开燃烧室组件。 排气室被定向为使得通过该排气室的废气沿大致平行于穿过第二燃烧室的气体的方向行进。 限定燃烧室的壁限定第二多个稀释氧化剂吸入孔，使得氧化剂可以稀释通过该室的废气。

    Gas turbine combustion chamber wall structure for minimizing cooling film disturbances
    6.
    发明授权
    Gas turbine combustion chamber wall structure for minimizing cooling film disturbances 失效
    用于最小化冷却膜的气体涡轮机燃烧室壁结构

    公开(公告)号：US5209067A

    公开(公告)日：1993-05-11

    申请号：US778283

    申请日：1991-10-17

    申请人： Gerard Y. G. Barbier ,  Frederic; B. Beule ,  Michel A. A. Desaulty ,  Jean M. C. M. P. Latour ,  Bruno R. H. Masse

    发明人： Gerard Y. G. Barbier ,  Frederic; B. Beule ,  Michel A. A. Desaulty ,  Jean M. C. M. P. Latour ,  Bruno R. H. Masse

    IPC分类号： F23R3/06 ,  F23R3/08

    CPC分类号： F23R3/06 ,  F23R3/08 ,  Y02T50/675

    摘要： A combustion chamber wall structure is formed of a plurality of segments, each segment having an upstream portion and a downstream portion. The upstream portion is attached to an outer surface of an adjacent wall segment at its downstream portion in an overlapping fashion such that the overlapping portions form a cooling air chamber. The main cooling air holes are defined by the upstream portion so as to communicate with the cooling chamber, which has an exit to direct the cooling air along an inner surface of the downstream portion of the wall segment. A primary air hole is defined by the downstream portion of the segment and is located adjacent to the main cooling air holes. This location maximizes the distance between the primary air hole and an upstream portion of the same segment, which, in turn, maximizes the distance along the inner surface of the segment on which the cooling air may flow without being disrupted by air passing through the primary air hole. The guidance of the primary/dilution air streams can also be carried out by a portion of the downstream air cooling film.

    摘要翻译： 燃烧室壁结构由多个段形成，每个段具有上游部分和下游部分。 上游部分以其重叠的方式在其下游部分处附接到相邻壁段的外表面，使得重叠部分形成冷却空气室。 主冷却空气孔由上游部分限定，以便与具有出口的冷却室连通，以沿着壁段的下游部分的内表面引导冷却空气。 一个主要空气孔由该段的下游部分限定，并且位于主冷却空气孔附近。 该位置使得主空气孔和同一段的上游部分之间的距离最大化，这又使得沿着冷却空气可流动的段的内表面的距离最大化，而不会被穿过主要空气的空气中断 气孔。 初级/稀释气流的引导也可以由下游空气冷却膜的一部分进行。

    Gas turbine engine combustion chamber with oxidizer intake flow control
    8.
    发明授权
    Gas turbine engine combustion chamber with oxidizer intake flow control 失效
    燃气涡轮发动机燃烧室与氧化剂进气流量控制

    公开(公告)号：US5235805A

    公开(公告)日：1993-08-17

    申请号：US851167

    申请日：1992-03-12

    申请人： Gerard Y. G. Barbier ,  Xavier M. H. Bardey ,  Michel A. A. Desaulty ,  Serge M. Meunier

    发明人： Gerard Y. G. Barbier ,  Xavier M. H. Bardey ,  Michel A. A. Desaulty ,  Serge M. Meunier

    IPC分类号： F23R3/04 ,  F23R3/26

    CPC分类号： F23R3/045 ,  F23R3/26

    摘要： An oxidizer intake flow control system is disclosed for a gas turbine engine combustion chamber. The chamber has an oxidizer intake assembly which extends through the wall of the chamber such that an inlet aperture of the oxidizer intake and an exhaust aperture of the oxidizer intake are located on opposite sides of the wall defining the combustion chamber. An oxidizer intake sleeve defines a central passage through which oxidizer may pass into the combustion chamber. The intake passage extends along a central axis and the intake assembly is attached to the wall of the combustion chamber such that it is rotatable about this central axis. The inlet aperture and/or the exhaust aperture is located in a plane extending non-perpendicularly to the central axis. The combustion chamber may have several oxidizer intake assemblies extending through the combustion chamber walls. The intake assemblies may be interconnected such that they may be simultaneously rotated with respect to the combustion chamber wall.

    摘要翻译： 公开了一种用于燃气涡轮发动机燃烧室的氧化剂进气流量控制系统。 腔室具有氧化剂进入组件，其延伸穿过腔室的壁，使得氧化剂吸入口的入口孔和氧化剂吸入口的排气口位于限定燃烧室的壁的相对侧上。 氧化剂进气套限定了中心通道，氧化剂可通过该中心通道进入燃烧室。 进气通道沿中心轴线延伸，并且进气组件附接到燃烧室的壁，使得其可围绕该中心轴线旋转。 入口孔和/或排气孔位于非垂直于中心轴延伸的平面中。 燃烧室可以具有延伸穿过燃烧室壁的几个氧化剂进料组件。 进气组件可以互连，使得它们可以相对于燃烧室壁同时旋转。

    Combustion chamber structure for a turbojet engine
    9.
    发明授权
    Combustion chamber structure for a turbojet engine 失效
    涡轮喷气发动机的燃烧室结构

    公开(公告)号：US4805397A

    公开(公告)日：1989-02-21

    申请号：US56884

    申请日：1987-06-03

    申请人： Gerard Y. G. Barbier ,  Gerard J. P. B. Laboure ,  Michel A. A. Desaulty ,  Francois Duchene ,  Pascal M. Truvillot

    发明人： Gerard Y. G. Barbier ,  Gerard J. P. B. Laboure ,  Michel A. A. Desaulty ,  Francois Duchene ,  Pascal M. Truvillot

    IPC分类号： F23R3/00 ,  F23R3/04 ,  F02C7/20 ,  F02C1/00

    CPC分类号： F23R3/045 ,  F23R3/002 ,  F05B2260/201 ,  F05B2260/202

    摘要： A combustion chamber for a turbojet engine is disclosed which utilizes double walled construction. Hot walls are attached to adjacent cold walls solely by an orifice member which defines an orifice to supply primary of dilution air to the combustion chamber. The attachment allows relative radial movement of the hot walls with respect to the cold walls so as to accommodate the thermal expansion and contraction of the hot walls. The sleeves forming the walls also cooperate so as to provide an internal cooling film on the interior surface of the hot walls. Convection cooling may also be utilized between the walls to prevent structural damage due to high temperatures.

    摘要翻译： 公开了一种用于涡轮喷气发动机的燃烧室，其采用双壁结构。 热壁仅通过孔口构件附接到相邻的冷壁，孔口构件限定了向燃烧室供应初级稀释空气的孔口。 附件允许热壁相对于冷壁的相对径向运动，以适应热壁的热膨胀和收缩。 形成壁的套筒也配合，以在热壁的内表面上提供内部冷却膜。 也可以在壁之间使用对流冷却，以防止由于高温引起的结构损坏。

    Combustion chamber with axially displaced fuel injectors
    10.
    发明授权
    Combustion chamber with axially displaced fuel injectors 失效
    具有轴向位移燃料喷射器的燃烧室

    公开(公告)号：US5335491A

    公开(公告)日：1994-08-09

    申请号：US118249

    申请日：1993-09-09

    申请人： Gerard Y. G. Barbier ,  Xavier M. H. Bardey ,  Michel A. A. Desaulty

    发明人： Gerard Y. G. Barbier ,  Xavier M. H. Bardey ,  Michel A. A. Desaulty

    IPC分类号： F23R3/34 ,  F23R3/42 ,  F23R3/48

    CPC分类号： F23R3/42 ,  F23R3/34 ,  F23R3/48

    摘要： A generally annular combustion chamber for a gas turbine engine is disclosed in which a plurality of generally cylindrical walls extend forwardly from an upstream end wall of the combustion chamber such that each cylindrical wall defines a cavity which is in communication with the interior of the combustion chamber. A first fuel injection head is located in each of the cylindrical walls so as to inject fuel into the cavity which is mixed with air and passes into the combustion chamber. The first fuel injection heads are located at a first axial position with respect to a longitudinal axis passing through the combustion chamber. A plurality of second fuel injection heads are located adjacent to the upstream end wall of the combustion chamber so as to spray fuel directly into the combustion chamber. The second fuel injection heads are located axially downstream of the axial positions of the first fuel injection heads.

    摘要翻译： 公开了一种用于燃气涡轮发动机的大体上环形的燃烧室，其中多个大致圆柱形的壁从燃烧室的上游端壁向前延伸，使得每个圆柱形壁限定了与燃烧室内部连通的空腔 。 第一燃料喷射头位于每个圆柱形壁中，以将燃料喷射到与空气混合并进入燃烧室的空腔中。 第一燃料喷射头位于相对于穿过燃烧室的纵向轴线的第一轴向位置。 多个第二燃料喷射头位于燃烧室的上游端壁附近，以将燃料直接喷入燃烧室。 第二燃料喷射头位于轴向位于第一燃料喷射头的轴向位置的下游。