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    DEVICE FOR INJECTING A MIXTURE OF AIR AND FUEL, AND COMBUSTION CHAMBER AND TURBOMACHINE PROVIDED WITH SUCH A DEVICE
    1.
    发明申请
    DEVICE FOR INJECTING A MIXTURE OF AIR AND FUEL, AND COMBUSTION CHAMBER AND TURBOMACHINE PROVIDED WITH SUCH A DEVICE 有权
    用于喷射空气和燃料混合物的设备，以及提供给这些设备的燃烧室和涡轮机

    公开(公告)号：US20080000234A1

    公开(公告)日：2008-01-03

    申请号：US11768421

    申请日：2007-06-26

    申请人： Patrice Andre COMMARET ,  Dominique Guezengar ,  Didier Hippolyte Hernandez ,  Romain Nicolas Lunel ,  Pascale Rollet

    发明人： Patrice Andre COMMARET ,  Dominique Guezengar ,  Didier Hippolyte Hernandez ,  Romain Nicolas Lunel ,  Pascale Rollet

    IPC分类号： F23R3/04

    CPC分类号： F23D11/107 ,  F23D14/78 ,  F23D2214/00 ,  F23R3/12 ,  F23R3/14 ,  F23R3/286 ,  Y02T50/675

    摘要： The invention relates to a device for injecting an air/fuel mixture into a combustion chamber, which is to be mounted within a restricted space. This injection device (20) comprises a bowl (70) having an external cylindrical wall (73) continued at its downstream end by a divergent section (74) provided, downstream, with a collar (75) having the form of a ring extending radially outward, the divergent section of the bowl being connected, immediately upstream of the flange, by a connecting wall (76) to a cylindrical ring (77), the cylindrical ring and the connecting wall forming a connection rim oriented in the upstream direction. At least one row of vortex holes (79) is formed in the external cylindrical wall, close to its upstream end, and the connecting wall of the connection rim of the bowl is provided with a row of cooling orifices (81) inclined axially at an angle y to the axis of symmetry of the injection device.

    摘要翻译： 本发明涉及一种用于将空气/燃料混合物喷射到要安装在受限空间内的燃烧室中的装置。 该注射装置（20）包括碗（70），其具有外部圆柱形壁（73），该外圆柱形壁（73）在其下游端通过扩散部分（74）延伸，所述扩散部分（74）在下游具有环形形式的环（75） 向外，碗的发散部分通过连接壁（76）直接连接到凸缘的上游，圆柱形环（77），圆柱形环和连接壁形成沿上游方向定向的连接边缘。 至少一排涡流孔（79）形成在外圆柱形壁上，靠近其上游端，并且碗的连接边缘的连接壁设置有一排沿轴向倾斜的冷却孔（81） 与注射装置的对称轴成y角。

    Device for injecting a mixture of air and fuel, and combustion chamber and turbomachine provided with such a device
    2.
    发明授权
    Device for injecting a mixture of air and fuel, and combustion chamber and turbomachine provided with such a device 有权
    用于喷射空气和燃料的混合物的装置，以及具有这种装置的燃烧室和涡轮机

    公开(公告)号：US07926281B2

    公开(公告)日：2011-04-19

    申请号：US11768421

    申请日：2007-06-26

    申请人： Patrice Andre Commaret ,  Dominique Guezengar ,  Didier Hippolyte Hernandez ,  Romain Nicolas Lunel ,  Pascale Rollet

    发明人： Patrice Andre Commaret ,  Dominique Guezengar ,  Didier Hippolyte Hernandez ,  Romain Nicolas Lunel ,  Pascale Rollet

    IPC分类号： F02C1/00 ,  F02G3/00

    CPC分类号： F23D11/107 ,  F23D14/78 ,  F23D2214/00 ,  F23R3/12 ,  F23R3/14 ,  F23R3/286 ,  Y02T50/675

    摘要： A device for injecting an air/fuel mixture into a combustion chamber mounted within a restricted space is disclosed. This injection device includes a bowl having an external cylindrical wall continued at its downstream end by a divergent section provided, downstream, with a collar having the form of a ring extending radially outward. The divergent section of the bowl is connected, immediately upstream of the flange, by a connecting wall to a cylindrical ring. The cylindrical ring and the connecting wall form a connection rim oriented in the upstream direction. At least one row of vortex holes is formed in the external cylindrical wall, close to its upstream end, and the connecting wall of the connection rim of the bowl is provided with a row of cooling orifices inclined axially at an angle γ to the axis of symmetry of the injection device.

    摘要翻译： 公开了一种用于将空气/燃料混合物注入安装在限制空间内的燃烧室中的装置。 该注射装置包括具有外圆柱形壁的碗，该外壁在其下游端由在下游具有径向向外延伸的环的形式的下游设置的扩散部分延伸。 碗的发散部分在紧邻法兰上游的连接壁连接到圆柱形环上。 圆柱形环和连接壁形成沿上游方向定向的连接边缘。 在外圆柱壁上形成至少一排涡流孔，靠近其上游端，并且碗的连接边缘的连接壁设置有一排冷却孔，该冷却孔轴向以与轴线 注射装置的对称性。

    CHAMBER-BOTTOM BAFFLE, COMBUSTION CHAMBER COMPRISING SAME AND GAS TURBINE ENGINE FITTED THEREWITH
    3.
    发明申请
    CHAMBER-BOTTOM BAFFLE, COMBUSTION CHAMBER COMPRISING SAME AND GAS TURBINE ENGINE FITTED THEREWITH 审中-公开
    箱体底部，包括相同的燃烧室和燃气涡轮发动机

    公开(公告)号：US20090019856A1

    公开(公告)日：2009-01-22

    申请号：US12165995

    申请日：2008-07-01

    申请人： Patrice Andre Commaret ,  Didier Hippolyte Hernandez ,  Romain Nicolas Lunel

    发明人： Patrice Andre Commaret ,  Didier Hippolyte Hernandez ,  Romain Nicolas Lunel

    IPC分类号： F23R3/42

    CPC分类号： F23R3/04 ,  F23R3/002 ,  F23R3/10 ,  F23R3/50

    摘要： The present invention relates to a baffle (10) for the bottom of a combustion chamber of a gas turbine engine, comprising a flat portion of wall (10a) with an opening for an injector of the combustion chamber to pass through, two longitudinal edges (10c, 10d) for the assembly to two adjacent baffles and two transverse edges (10e, 10f), wherein at least one of the edges comprises a joint cover (10d1) arranging a housing (10d10) along said edge for an edge (10′c) of an adjacent baffle (10′) so as to seal the junction between the two edges. The invention also relates to a combustion chamber incorporating said baffles.

    摘要翻译： 本发明涉及一种用于燃气涡轮发动机的燃烧室的底部的挡板（10），其包括具有用于燃烧室的喷射器通过的开口的壁（10a）的平坦部分，两个纵向边缘 10e，10d），用于组装到两个相邻的挡板和两个横向边缘（10e，10f），其中至少一个边缘包括沿着所述边缘设置壳体（10d10）的接合盖（10d1），用于边缘（10' c）相邻的挡板（10'），以便密封两个边缘之间的接合部。 本发明还涉及包含所述挡板的燃烧室。

    Turbomachine diffuser
    6.
    发明授权
    Turbomachine diffuser 有权
    涡轮机扩散器

    公开(公告)号：US08047777B2

    公开(公告)日：2011-11-01

    申请号：US12190105

    申请日：2008-08-12

    申请人： Patrice Andre Commaret ,  Michel Andre Albert Desaulty ,  Romain Nicolas Lunel ,  Pascale Rollet

    发明人： Patrice Andre Commaret ,  Michel Andre Albert Desaulty ,  Romain Nicolas Lunel ,  Pascale Rollet

    IPC分类号： F04D29/44 ,  F04D29/54 ,  F03B1/00 ,  F03B11/02 ,  F03B5/00

    CPC分类号： F02C3/08 ,  F02C3/14 ,  F04D29/444 ,  F05D2250/71

    摘要： A turbomachine comprising an annular combustion chamber (40) with injection orifices (44); a centrifugal compressor (10) having a centrifugal downstream stage and an annular diffuser (20) comprising: a radially-oriented upstream portion (21)with diffusion passages (22) connected to the outlet of the compressor and an elbow-shaped intermediate portion (24)and a downstream portion (25) comprising a series of flow-straightening vanes (26) and inclined relative to the axis (A) of the turbomachine. In the section plane containing the axis (A) of the turbomachine and passing via the center (C) of one of said injection orifices (44), the curvilinear abscissa distance along a flow line (L) between the middle (0) of the flow path at the trailing edges of the flow-straightening vanes (26) and said center (C) is greater than or equal to three times the height (h) of said flow path.

    摘要翻译： 一种涡轮机，包括具有喷射孔（44）的环形燃烧室（40）; 具有离心下游级的离心式压缩机（10）和环形扩散器（20），包括：径向定向的上游部分（21），其具有连接到压缩机出口的扩散通道（22）和肘形中间部分 24）和包括一系列流动矫直叶片（26）并相对于涡轮机的轴线（A）倾斜的下游部分（25）。 在包含涡轮机的轴线（A）并且经过所述喷射孔（44）中的一个的中心（C）的截面中，沿着沿着所述喷嘴的中间（0）之间的流动线（L）的曲线横坐标距离 在流动矫正叶片（26）和所述中心（C）的后缘处的流动路径大于或等于所述流动路径的高度（h）的三倍。

    TURBOMACHINE DIFFUSER
    7.
    发明申请
    TURBOMACHINE DIFFUSER 有权
    涡轮增压器

    公开(公告)号：US20090047127A1

    公开(公告)日：2009-02-19

    申请号：US12190105

    申请日：2008-08-12

    申请人： Patrice Andre Commaret ,  Michel Andre Albert Desaulty ,  Romain Nicolas Lunel ,  Pascale Rollet

    发明人： Patrice Andre Commaret ,  Michel Andre Albert Desaulty ,  Romain Nicolas Lunel ,  Pascale Rollet

    IPC分类号： F01D9/02

    CPC分类号： F02C3/08 ,  F02C3/14 ,  F04D29/444 ,  F05D2250/71

    摘要： A turbomachine comprising: an annular combustion chamber (40) with injection orifices (44); a centrifugal compressor (10) having a centrifugal downstream stage; and an annular diffuser (20) comprising: a radially-oriented upstream portion (21) with diffusion passages (22) connected to the outlet of the compressor; an elbow-shaped intermediate portion (24); and a downstream portion (25) comprising a series of flow-straightening vanes (26) and inclined relative to the axis (A) of the turbomachine. In the section plane containing the axis (A) of the turbomachine and passing via the center (C) of one of said injection orifices (44), the curvilinear abscissa distance along a flow line (L) between the middle (O) of the flow path at the trailing edges of the flow-straightening vanes (26) and said center (C) is greater than or equal to three times the height (h) of said flow path.

    摘要翻译： 一种涡轮机，包括：具有喷射孔（44）的环形燃烧室（40）; 具有离心下游级的离心式压缩机（10） 和环形扩散器（20），包括：径向定向的上游部分（21），其具有连接到压缩机出口的扩散通道（22） 肘形中间部分（24）; 以及包括一系列流动整流叶片（26）并相对于涡轮机的轴线（A）倾斜的下游部分（25）。 在包含涡轮机的轴线（A）并且经过所述喷射孔（44）中的一个的中心（C）的截面中，沿着沿着所述喷射孔（44）的中间（O）的流线（L）的曲线横坐标距离 在流动矫正叶片（26）和所述中心（C）的后缘处的流动路径大于或等于所述流动路径的高度（h）的三倍。

    GAS TURBINE ENGINE COMBUSTION CHAMBER COMPRISING CMC DEFLECTORS
    10.
    发明申请
    GAS TURBINE ENGINE COMBUSTION CHAMBER COMPRISING CMC DEFLECTORS 有权
    气体涡轮发动机燃烧室包括CMC偏转器

    公开(公告)号：US20110113789A1

    公开(公告)日：2011-05-19

    申请号：US12997266

    申请日：2009-06-10

    申请人： Sylvain Duval ,  Didier Hippolyte Hernandez ,  Romain Nicolas Lunel

    发明人： Sylvain Duval ,  Didier Hippolyte Hernandez ,  Romain Nicolas Lunel

    IPC分类号： F02C7/20 ,  F01D1/02

    CPC分类号： F23R3/283

    摘要： A gas turbine engine combustion chamber including at least one deflector mounted on the chamber end wall and including an opening for a carburetted air supply device. The deflector includes an opening, corresponding to the chamber end wall opening, with an annular cylindrical part for attachment to the wall, the cylindrical part including a mechanical attachment mechanism collaborating with a complementary attachment mechanism on a metal sleeve secured to the wall and a cylindrical centering cup fixed by one end to the sleeve and housed inside the cylindrical part of the deflector.

    摘要翻译： 一种燃气涡轮发动机燃烧室，包括安装在室端壁上的至少一个偏转器，并且包括用于碳化空气供应装置的开口。 偏转器包括对应于室端壁开口的开口，具有用于附接到壁的环形圆柱形部分，圆柱形部分包括与固定到壁上的金属套筒上的互补附接机构协作的机械附接机构，以及圆柱形 定心杯由一端固定到套筒上并容纳在偏转器的圆柱形部分内。