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18 条记录 (耗时 0.025 秒)

    Method and apparatus for water injection via primary jets
    3.
    发明授权
    Method and apparatus for water injection via primary jets 失效
    通过主喷射器注水的方法和装置

    公开(公告)号：US6112511A

    公开(公告)日：2000-09-05

    申请号：US138192

    申请日：1998-08-21

    申请人： Geoffrey D. Myers

    发明人： Geoffrey D. Myers

    IPC分类号： F01D9/06 ,  F02C3/30 ,  F23L7/00 ,  F02C7/00

    CPC分类号： F02C3/305 ,  F01D9/065 ,  F02C3/30 ,  F23L7/002

    摘要： An apparatus is disclosed for injecting fluid coolant into a gas turbine engine combustion system at a location distal the fuel nozzle, such as at the primary or dilution orifices of the combustor. In one embodiment of the invention, the apparatus comprises a substantially hollow cylindrical tube adapted for insertion into a primary jet orifice of the combustor. A water nozzle is housed at the end of the tube opposite the primary jet orifice. The water nozzle is positionally adjustable relative to the inner liner. A pair of apertures is disposed along the tube between the primary jet orifice and the water nozzle so as to admit primary jet air from the plenum surrounding the combustion chamber into the tube. The apertures are configured to impart a swirling motion to the primary jet air as it enters the tube. Alternatively, at least one baffle may be housed within the tube proximal the aperture to impart a swirling motion to fluid communicated to the tube by the plenum. The water nozzle mixes water with the swirling air in the tube prior to the swirling air being admitted into the combustor through the primary air jet orifice. By pre-mixing the water with primary air, the need for complicated water/fuel injectors is obviated and the problems associated with injecting water proximal the fuel injector are eliminated.

    摘要翻译： 公开了一种用于将燃料涡轮发动机燃烧系统中的流体冷却剂喷射到燃料喷嘴远侧的位置，例如在燃烧器的初级或稀释孔处。 在本发明的一个实施例中，该装置包括适于插入燃烧器的主喷射孔的基本中空的圆柱形管。 水喷嘴容纳在与主喷射口相对的管的端部处。 水嘴相对于内衬可位置调节。 沿着管子在一次喷射孔和水喷嘴之间设置一对孔口，以便将一次喷射空气从围绕燃烧室的气室引入管中。 孔被构造成在初级喷射空气进入管时赋予旋转运动。 或者，至少一个挡板可以容纳在靠近孔的管内，以对通过气室与管连通的流体进行旋转运动。 在旋转空气通过一次空气喷射口进入燃烧器之前，水喷嘴将水与管中的旋转空气混合。 通过将水与一次空气预混合，消除了对复杂的水/燃料喷射器的需要，并且消除了与注入燃料喷射器的水相关的问题。

    Reduced diameter annular combustor
    4.
    发明授权
    Reduced diameter annular combustor 失效
    直径减小的环形燃烧器

    公开(公告)号：US5331805A

    公开(公告)日：1994-07-26

    申请号：US52417

    申请日：1993-04-22

    申请人： Geoffrey D. Myers ,  Manuel M. Cardenas, Jr.

    发明人： Geoffrey D. Myers ,  Manuel M. Cardenas, Jr.

    IPC分类号： F23R3/14 ,  F23R3/50

    CPC分类号： F23R3/50 ,  F23R3/14 ,  Y02T50/675

    摘要： An annular gas turbine engine combustor includes additional axial primary airflow openings, formed as arcuately segmented openings on opposite sides of each of the airblast fuel nozzles of the combustor, for reducing overall combustor diameter while maintaining flame stabilization and avoiding unacceptable thermal variations in the combustion process.

    摘要翻译： 环形燃气涡轮发动机燃烧器包括另外的轴向主要气流开口，在燃烧器的每个喷气燃料喷嘴的相对侧形成弧形分段的开口，用于在保持火焰稳定性的同时减少燃烧室直径，并避免燃烧过程中不可接受的热变化 。

    Axial Flow Fuel Nozzle with a Stepped Center Body
    5.
    发明申请
    Axial Flow Fuel Nozzle with a Stepped Center Body 有权
    具有阶梯式中心体的轴流式燃油喷嘴

    公开(公告)号：US20130186094A1

    公开(公告)日：2013-07-25

    申请号：US13354897

    申请日：2012-01-20

    申请人： Nishant Govindbhai Parsania ,  Geoffrey D. Myers ,  Gregory Allen Boardman

    发明人： Nishant Govindbhai Parsania ,  Geoffrey D. Myers ,  Gregory Allen Boardman

    IPC分类号： F23R3/14

    CPC分类号： F23R3/286 ,  F23D11/16 ,  F23L7/002 ,  F23R3/14

    摘要： An axial flow fuel nozzle for a gas turbine includes a plurality of annular passages for delivering materials for combustion. An annular air passage receives compressor discharge air, and a plurality of swirler vane slots are positioned adjacent an axial end of the annular air passage. A first next annular passage is disposed radially inward of the annular air passage and includes first openings positioned adjacent an axial end of the first annular passage and downstream of the swirler vane slots. A second next annular passage is disposed radially inward of the first annular passage and includes second openings positioned adjacent an axial end of the second annular passage and downstream of the first openings.

    摘要翻译： 用于燃气轮机的轴流式燃料喷嘴包括用于输送用于燃烧的材料的多个环形通道。 环形空气通道接收压缩机排放空气，并且多个旋流器叶片槽邻近环形空气通道的轴向端定位。 第一个下一个环形通道设置在环形空气通道的径向内侧，并且包括邻近第一环形通道的轴向端部并且位于旋流器叶片槽的下游的第一开口。 第二个下一个环形通道设置在第一环形通道的径向内侧，并且包括邻近第二环形通道的轴向端部和第一开口下游定位的第二开口。

    Fuel nozzle and diffusion tip therefor
    6.
    发明授权
    Fuel nozzle and diffusion tip therefor 有权
    燃油喷嘴和扩散头

    公开(公告)号：US07861528B2

    公开(公告)日：2011-01-04

    申请号：US11892298

    申请日：2007-08-21

    申请人： Geoffrey D. Myers ,  Scott Simmons ,  Stephen R. Thomas

    发明人： Geoffrey D. Myers ,  Scott Simmons ,  Stephen R. Thomas

    IPC分类号： F02C1/00

    CPC分类号： F23R3/28 ,  F23D11/38 ,  F23D2209/30 ,  F23D2900/00018

    摘要： A fuel nozzle having a dedicated circuit to cool the diffusion tip with lower part count and reduced complexity. More specifically, the proposed design uses an independent circuit to cool the tip with diffusion fuel or purge air. An impingement plate may be provided to augment the cooling effect.

    摘要翻译： 具有专用电路的燃料喷嘴，其具有以较低部件数量和降低的复杂度来冷却扩散尖端。 更具体地，所提出的设计使用独立的电路来用扩散燃料或吹扫空气来冷却尖端。 可以提供冲击板以增加冷却效果。

    FUEL NOZZLE ASSEMBLY FOR USE WITH A GAS TURBINE ENGINE AND METHOD OF ASSEMBLING SAME
    7.
    发明申请
    FUEL NOZZLE ASSEMBLY FOR USE WITH A GAS TURBINE ENGINE AND METHOD OF ASSEMBLING SAME 失效
    用于燃气涡轮发动机的燃料喷嘴组件及其组装方法

    公开(公告)号：US20100107639A1

    公开(公告)日：2010-05-06

    申请号：US12265233

    申请日：2008-11-05

    申请人： Geoffrey D. Myers ,  Scott Simmons ,  Stephen R. Thomas ,  Donald Mark Bailey

    发明人： Geoffrey D. Myers ,  Scott Simmons ,  Stephen R. Thomas ,  Donald Mark Bailey

    IPC分类号： F02C7/22 ,  B05B15/00 ,  F23R3/28

    CPC分类号： F23R3/28 ,  F16L9/02 ,  F16L9/18 ,  F16L51/00 ,  F23D14/46 ,  F23D2206/10 ,  F23D2211/00 ,  F23D2212/20 ,  F23R2900/00005

    摘要： A fuel nozzle configured to channel fluid toward a combustion chamber within a gas turbine engine and a method for assembling the same are provided. The fuel nozzle includes a first hollow tube fabricated from a first material that has a first coefficient of thermal expansion and a second tube fabricated from a second material that has a second coefficient of thermal expansion that is different from the first coefficient of thermal expansion. The second tube is coupled within the first tube such that the first tube substantially circumscribes the second tube, and the second tube thermally expands approximately at a same rate as the first tube during fuel nozzle operation.

    摘要翻译： 提供了一种构造成将流体引导到燃气涡轮发动机内的燃烧室的燃料喷嘴及其组装方法。 燃料喷嘴包括由具有第一热膨胀系数的第一材料制成的第一中空管和由具有不同于第一热膨胀系数的第二热膨胀系数的第二材料制成的第二管。 第二管联接在第一管内，使得第一管基本上包围第二管，并且第二管在燃料喷嘴操作期间以与第一管相同的速率大约膨胀。

    Combustor with fuel preparation chambers
    8.
    发明授权
    Combustor with fuel preparation chambers 有权
    带燃料准备室的燃烧器

    公开(公告)号：US06286300B1

    公开(公告)日：2001-09-11

    申请号：US09492678

    申请日：2000-01-27

    申请人： Joseph Zelina ,  Geoffrey D. Myers ,  Ram Srinivasan ,  Robert S. Reynolds

    发明人： Joseph Zelina ,  Geoffrey D. Myers ,  Ram Srinivasan ,  Robert S. Reynolds

    IPC分类号： F23R330

    CPC分类号： F23R3/14 ,  Y02T50/675

    摘要： An annular combustor having fuel preparation chambers mounted in the dome of the combustor. The fuel preparation chamber comprises an annular wall extending axially from an inlet to an exit that defines a mixing chamber. Mounted to the inlet are an air swirler and a fuel atomizer. The air swirler provides swirled air to the mixing chamber while the atomizer provides a fuel spray. On the downstream side of the exit, the fuel preparation chamber has an inwardly extending conical wall that compresses the swirling mixture of fuel and air exiting the mixing chamber.

    摘要翻译： 具有安装在燃烧器的圆顶中的燃料准备室的环形燃烧器。 燃料制备室包括从入口轴向延伸到限定混合室的出口的环形壁。 安装到入口的是空气旋流器和燃料雾化器。 空气旋流器为混合室提供旋转空气，而雾化器提供燃料喷雾。 在出口的下游侧，燃料准备室具有向内延伸的锥形壁，其压缩离开混合室的燃料和空气的旋转混合物。

    Axial flow fuel nozzle with a stepped center body
    9.
    发明授权
    Axial flow fuel nozzle with a stepped center body 有权
    具有阶梯式中心体的轴流燃油喷嘴

    公开(公告)号：US09217570B2

    公开(公告)日：2015-12-22

    申请号：US13354897

    申请日：2012-01-20

    申请人： Nishant Govindbhai Parsania ,  Geoffrey D. Myers ,  Gregory Allen Boardman

    发明人： Nishant Govindbhai Parsania ,  Geoffrey D. Myers ,  Gregory Allen Boardman

    IPC分类号： F02C3/30 ,  F23R3/14 ,  F23R3/28 ,  F23L7/00 ,  F23D11/16

    CPC分类号： F23R3/286 ,  F23D11/16 ,  F23L7/002 ,  F23R3/14

    摘要： An axial flow fuel nozzle for a gas turbine includes a plurality of annular passages for delivering materials for combustion. An annular air passage receives compressor discharge air, and a plurality of swirler vane slots are positioned adjacent an axial end of the annular air passage. A first next annular passage is disposed radially inward of the annular air passage and includes first openings positioned adjacent an axial end of the first annular passage and downstream of the swirler vane slots. A second next annular passage is disposed radially inward of the first annular passage and includes second openings positioned adjacent an axial end of the second annular passage and downstream of the first openings.

    摘要翻译： 用于燃气轮机的轴流式燃料喷嘴包括用于输送用于燃烧的材料的多个环形通道。 环形空气通道接收压缩机排放空气，并且多个旋流器叶片槽邻近环形空气通道的轴向端定位。 第一个下一个环形通道设置在环形空气通道的径向内侧，并且包括邻近第一环形通道的轴向端部并且位于旋流器叶片槽的下游的第一开口。 第二个下一个环形通道设置在第一环形通道的径向内侧，并且包括邻近第二环形通道的轴向端部和第一开口下游定位的第二开口。