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    Air flow conditioner for a combustor can of a gas turbine engine
    1.
    发明申请
    Air flow conditioner for a combustor can of a gas turbine engine 有权
    用于燃气涡轮发动机的燃烧室的气流调节器

    公开(公告)号：US20070227148A1

    公开(公告)日：2007-10-04

    申请号：US11397364

    申请日：2006-04-04

    申请人： Robert Bland ,  John Battaglioli ,  Anil Gulati ,  Stephen Ramier

    发明人： Robert Bland ,  John Battaglioli ,  Anil Gulati ,  Stephen Ramier

    IPC分类号： F23R3/00

    CPC分类号： F23R3/04

    摘要： A burner (27) of a gas turbine engine (10) includes a cylindrical basket (60) comprising an air flow reversal region (86). The flow reversal region ends at an air inlet plane (84) of the basket. The burner also includes a flow conditioner (90) disposed in the flow reversal region transecting an air flow (80) flowing non-uniformly through the flow reversal region, the flow conditioner being effective to mitigate variation of the air flow entering the basket across the inlet plane.

    摘要翻译： 燃气涡轮发动机（10）的燃烧器（27）包括包括气流反转区域（86）的圆柱形篮（60）。 流动反转区域在篮的空气入口平面（84）处终止。 燃烧器还包括设置在流动反向区域中的流动调节器（90），其横切不均匀地流过流动反向区域的空气流（80），流动调节器有效地减轻进入篮子的空气流的变化 入口平面。

    Air flow conditioner for a combustor can of a gas turbine engine
    2.
    发明授权
    Air flow conditioner for a combustor can of a gas turbine engine 有权
    用于燃气涡轮发动机的燃烧室的气流调节器

    公开(公告)号：US07762074B2

    公开(公告)日：2010-07-27

    申请号：US11397364

    申请日：2006-04-04

    申请人： Robert J. Bland ,  John Battaglioli ,  Anil Gulati ,  Stephen Ramier

    发明人： Robert J. Bland ,  John Battaglioli ,  Anil Gulati ,  Stephen Ramier

    IPC分类号： F02C1/00 ,  F02G3/00

    CPC分类号： F23R3/04

    摘要： A burner (27) of a gas turbine engine (10) includes a cylindrical basket (60) comprising an air flow reversal region (86). The flow reversal region ends at an air inlet plane (84) of the basket. The burner also includes a flow conditioner (90) disposed in the flow reversal region transecting an air flow (80) flowing non-uniformly through the flow reversal region, the flow conditioner being effective to mitigate variation of the air flow entering the basket across the inlet plane.

    摘要翻译： 燃气涡轮发动机（10）的燃烧器（27）包括包括气流反转区域（86）的圆柱形篮（60）。 流动反转区域在篮的空气入口平面（84）处终止。 燃烧器还包括设置在流动反向区域中的流动调节器（90），其横切不均匀地流过流动反向区域的空气流（80），流动调节器有效地减轻进入篮子的空气流的变化 入口平面。

    Flashback resistant pre-mix burner for a gas turbine combustor
    3.
    发明授权
    Flashback resistant pre-mix burner for a gas turbine combustor 有权
    用于燃气轮机燃烧器的防反冲预燃烧器

    公开(公告)号：US06786047B2

    公开(公告)日：2004-09-07

    申请号：US10245768

    申请日：2002-09-17

    申请人： Robert Bland ,  Anil Gulati ,  John Battaglioli

    发明人： Robert Bland ,  Anil Gulati ,  John Battaglioli

    IPC分类号： F02C100

    CPC分类号： F23D14/82 ,  F23D2900/00008 ,  F23D2900/14004 ,  F23R3/14 ,  F23R3/286

    摘要： A pre-mixing burner (10) for a gas turbine engine having improved resistance to flashback. Fuel (32) is supplied to a pre-mixing chamber (24) of the burner from a plurality of fuel outlet openings (34) formed in fuel pegs (36) extending into the flow of air (30) passing through the chamber. The fuel outlet openings are formed to direct the fuel in a downstream direction at an angle (A) relative to the direction of the flow of air past the respective fuel peg. This angle imparts a downstream velocity vector (VD) for increasing the net velocity of the air and a normal velocity vector (VN) for directing the fuel away from the wake (44) formed downstream of the fuel peg. Alternate ones of the fuel outlet openings along a single fuel peg may be formed at respective positive (A) and negative (B) angles with respect to a plane (46) extending along the wake in order to minimize the size of the wake. The propensity of the burner to support upstream flame propagation and flashback is thus reduced by increasing the net air velocity, by minimizing the amount of fuel entrained in the wake, and by minimizing the size of the wake.

    摘要翻译： 一种用于燃气涡轮发动机的预混合燃烧器（10），其具有改进的抗回火性能。 燃料（32）从形成在延伸进入通过该室的空​​气流（30）的燃料栓（36）中的多个燃料出口（34）供应到燃烧器的预混合室（24）。 燃料出口开口形成为相对于通过相应的燃料栓的空气流的方向在下游方向上以相对于空气流的方向（A）引导燃料。 该角度赋予用于增加空气净速度的下游速度矢量（VD）和用于引导燃料远离形成在燃料栓的下游的尾流（44）的正常速度矢量（VN）。 沿着单个燃料栓的燃料出口开口中的替代燃料出口可相对于沿着尾流延伸的平面（46）以相对的正（A）和负（B）角度形成，以便最小化尾流的尺寸。 燃烧器支持上游火焰传播和回火的倾向因此通过增加净空气速度来减少，通过最小化在尾流中夹带的燃料的量以及通过使尾流的尺寸最小化来实现。

    Dynamics free low emissions gas turbine combustor
    8.
    发明授权
    Dynamics free low emissions gas turbine combustor 失效
    无动力低排放燃气轮机燃烧器

    公开(公告)号：US5644918A

    公开(公告)日：1997-07-08

    申请号：US337704

    申请日：1994-11-14

    申请人： Anil Gulati ,  Anthony John Dean ,  David Graham Holmes ,  Eayre Bruce Voorhees

    发明人： Anil Gulati ,  Anthony John Dean ,  David Graham Holmes ,  Eayre Bruce Voorhees

    IPC分类号： F23M99/00 ,  F23R3/00 ,  F23R3/02 ,  F23R3/18 ,  F02C7/045

    CPC分类号： F23R3/18 ,  F23M20/005 ,  F23R3/002 ,  F23R3/02 ,  F05B2260/96 ,  F23R2900/00014

    摘要： Combustion-induced instabilities are minimized in gas turbine combustors by incorporating one or more Helmholtz resonators into the combustor. First and second plates located in the head end of the combustor casing define one cavity, and a sleeve located between the casing and the liner defines another cavity. Each of the two cavities is connected to the combustion chamber by one or more throats, thus forming Helmholtz resonators. The throats of each resonator can be tubes of different lengths and/or different cross-sectional areas to provide dynamics suppression over a broad band of frequencies. The throats can also be arranged such that each throat is associated with a different portion of its respective cavity, each cavity portion having a different volume.

    摘要翻译： 通过将一个或多个亥姆霍兹共振器并入到燃烧器中，在燃气轮机燃烧器中燃烧诱发的不稳定性被最小化。 位于燃烧器壳体头部的第一和第二板限定一个空腔，并且位于壳体和衬套之间的套筒限定另一腔。 两个腔中的每一个通过一个或多个喉部连接到燃烧室，从而形成亥姆霍兹共振器。 每个谐振器的喉部可以是具有不同长度和/或不同横截面面积的管，以在宽频带上提供动态抑制。 喉部也可以布置成使得每个喉部与其相应空腔的不同部分相关联，每个空腔部分具有不同的体积。

    Asymmetric flameholder for gas turbine engine afterburner
    9.
    发明授权
    Asymmetric flameholder for gas turbine engine afterburner 失效
    燃气轮机发动机燃烧器不对称火焰稳定器

    公开(公告)号：US5095696A

    公开(公告)日：1992-03-17

    申请号：US459416

    申请日：1990-01-02

    申请人： Anil Gulati ,  Elwin C. Bigelow

    发明人： Anil Gulati ,  Elwin C. Bigelow

    IPC分类号： F23R3/18

    CPC分类号： F23R3/18

    摘要： An afterburner flameholder for a gas turbine engine having a central diffuser cone, a generally cylindrical outer shell and fuel spray bars between the shell and cone defining an afterburner region is provided, which comprise an annular member with an asymmetric V-shaped cross section. The annular member is adapted to be secured to the engine in the afterburner region with the apex of the V facing upstream in the axial direction toward the fuel spray bars. The annular member has a first and second circular sidewall member each joined at one end forming an apex, the annular member in cross section has unequal length sidewall members. The difference in length between the distal ends of the first and second circular sidewall members is sufficient to cause spanwise vortices shed at the distal ends of the sidewall members to be out of phase when they meet downstream from the flameholder. The different lengths of the distal ends of the sidewall members results in one sidewall member extending further from the apex than the other, situating the distal ends in different planes so that spanwise vortices shed from the asymmetric sidewall members travel different path lengths and are out of phase when they meet downstream.

    摘要翻译： 一种用于燃气涡轮发动机的加力燃烧器火焰发生器，其具有中心扩散器锥体，大致圆柱形外壳和限定加力燃烧器区域的壳体和锥体之间的燃料喷射杆，其包括具有不对称V形横截面的环形构件。 环形构件适于在加力器区域中固定到发动机，其中V形顶点朝向燃料喷杆在轴向方向上游。 环形构件具有第一和第二圆形侧壁构件，每个第一和第二圆形侧壁构件在一端形成顶点，横截面中的环形构件具有不等长的侧壁构件。 第一和第二圆形侧壁构件的远端之间的长度差异足以使侧壁构件的远端处的翼展旋转涡流在与火焰稳定器的下游相遇时脱离相位。 侧壁构件的远端的不同长度导致一个侧壁构件从顶点进一步延伸而不是另一个，将远端位于不同的平面中，使得从不对称侧壁构件脱落的翼展方向涡流行进不同的路径长度，并且离开 它们在下游相遇时。