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1. 发明授权

US06339923B1 Fuel air mixer for a radial dome in a gas turbine engine combustor 失效
标题翻译：用于燃气涡轮发动机燃烧器中的径向圆顶的燃料空气混合器
公开(公告)号：US06339923B1
公开(公告)日：2002-01-22
申请号：US09398559
申请日：1999-09-17
申请人： Ely E. Halila , Stuart C. Greenfield , Paul V. Heberling , John D. Bibler , John A. Kastl
发明人： Ely E. Halila , Stuart C. Greenfield , Paul V. Heberling , John D. Bibler , John A. Kastl
IPC分类号： F23R330
CPC分类号： F23R3/286 , F23R3/343 , F23R3/50
摘要： A fuel air mixer for a gas turbine engine combustor having a longitudinal axis therethrough, wherein the fuel air mixer is configured for use in a dome oriented substantially radial to the longitudinal axis. The fuel air mixer includes a fuel injection assembly having a first end, a second end, a fuel passage extending therethrough, and a flange portion having a plurality of spaced openings formed therein which extends from the first end. The fuel air mixer also includes a mixer assembly having a first end, a second end, a cavity formed in a central portion thereof, and a flange portion having a plurality of spaced openings formed therein which extends from the first end. The mixer assembly is configured to receive the fuel injection assembly in the cavity so that the fuel injection assembly and the mixer assembly are able to be connected to an outer casing of the combustor by means of the respective flange portions.
摘要翻译：一种用于燃气涡轮发动机燃烧器的燃料空气混合器，其具有穿过其的纵向轴线，其中所述燃料空气混合器构造成用于基本上径向于所述纵向轴线的圆顶。燃料空气混合器包括燃料喷射组件，其具有第一端，第二端，延伸穿过其中的燃料通道，以及在其中形成有从第一端延伸的多个间隔开口的凸缘部分。燃料空气混合器还包括具有第一端，第二端，形成在其中心部分中的空腔的混合器组件，以及形成在其中的从第一端延伸的多个间隔开口的凸缘部分。混合器组件构造成在空腔中接收燃料喷射组件，使得燃料喷射组件和混合器组件能够通过相应的凸缘部分连接到燃烧器的外壳。

2. 发明授权

US06530223B1 Multi-stage radial axial gas turbine engine combustor 有权
标题翻译：多级径向轴向燃气轮机发动机
公开(公告)号：US06530223B1
公开(公告)日：2003-03-11
申请号：US09398557
申请日：1999-09-17
申请人： Willard J. Dodds , Paul V. Heberling , Jack R. Taylor , Ely E. Halila
发明人： Willard J. Dodds , Paul V. Heberling , Jack R. Taylor , Ely E. Halila
IPC分类号： F02C100
CPC分类号： F23R3/286 , F23R3/343
摘要： A combustor for a gas turbine engine having a longitudinal axis therethrough, including an outer liner having a forward end and an aft end, an inner liner having a forward end and an aft end, a first dome formed upstream of the outer liner forward end so as to define a first combustion zone radially oriented to the longitudinal axis, and a dome plate having an outer portion connected to an upstream end of the first dome and an inner portion connected to the inner liner forward end, wherein a second combustion zone is defined by the dome plate, the outer liner, and the inner liner substantially perpendicular to the first combustion zone.
摘要翻译：一种用于燃气涡轮发动机的燃烧器，其具有穿过其的纵向轴线，包括具有前端和后端的外衬套，具有前端和后端的内衬，具有形成在外衬套前端上游的第一圆顶，以限定径向定向到纵向轴线的第一燃烧区，以及圆顶板，其外部部分连接到第一圆顶的上游端，内部部分连接到内衬前端，其中定义了第二燃烧区通过圆顶板，外衬套和内衬基本上垂直于第一燃烧区。

3. 发明授权

US5444982A Cyclonic prechamber with a centerbody 失效
标题翻译：带有中心体的旋风预制室
公开(公告)号：US5444982A
公开(公告)日：1995-08-29
申请号：US180245
申请日：1994-01-12
申请人： Paul V. Heberling , Mark P. Kelsey , Willard J. Dodds
发明人： Paul V. Heberling , Mark P. Kelsey , Willard J. Dodds
IPC分类号： F23D11/36 , F23D11/44 , F23R3/12 , F23R3/14 , F23R3/32
CPC分类号： F23R3/12 , F23D11/36 , F23D11/441 , F23R3/14 , Y02T50/675
摘要： The present invention provides a cyclonic precombustion mixing chamber or prechamber having an axially extending annular cyclonic chamber to vaporize liquid fuel therein and a centerbody centrally disposed within. A fuel injection means introduces liquid fuel radially outward into the cyclonic chamber. The centerbody extends axially through an annular exit of the prechamber to define a throat and throat exit therebetween which is optimally designed for preventing backflash and autoignition. In one embodiment the diameter of the throat is sized to substantially match the diameter of the potential core. The diameter of the potential core and the centerbody at the throat exit, D.sub.c, may given by the solution to the following equation;4(D.sub.c /D.sub.t).sup.4 =(.rho./.DELTA.P)V.sub.w.sup.2 (D.sub.w /D.sub.t).sup.2 [1+(D.sub.c /D.sub.t).sup.2 ]where D.sub.t is the diameter of the outer edge of the throat exit, .rho. is the density of the air (determined from the air pressure and temperature at the inlet of the prechamber), D.sub.w is the inside diameter of the cyclone as defined by a cyclonic chamber inlet, V.sub.w is the tangential velocity, and .DELTA.P is the total pressure drop across the combustor (about 5% of the total pressure of the compressor discharge flow in many aircraft gas turbine engine combustors).
摘要翻译：本发明提供了一种旋风预燃混合室或预燃室，其具有轴向延伸的环形旋风室，以使其中的液体燃料蒸发并且集中设置在其内的中心体。燃料喷射装置将液体燃料径向向外引入旋风室。中心体轴向延伸通过预制室的环形出口，以在其间限定出喉部和喉部出口，其最佳设计用于防止反向闪光和自燃。在一个实施例中，喉部的直径的尺寸被设计成基本匹配电位芯的直径。喉部出口处的电位核心和中心体的直径Dc可以通过以下方程式求解： 4（Dc / Dt）4 =（rho / DELTA P）Vw2（Dw / Dt）2 [1+（Dc / Dt）2]其中Dt是喉口出口的外边缘的直径，rho是空气（从空气压力和预制室入口处的温度确定），Dw是由旋风室入口限定的旋风分离器的内径，Vw是切向速度，DELTA P是整个压缩机的总压降燃烧器（在许多飞机燃气涡轮发动机燃烧器中压缩机排放流的总压力的约5％）。

4. 发明授权

US5680766A Dual fuel mixer for gas turbine combustor 失效
公开(公告)号：US5680766A
公开(公告)日：1997-10-28
申请号：US581818
申请日：1996-01-02
申请人： Narendra D. Joshi , Paul R. Angel , James M. Caldwell , Paul V. Heberling , Anthony J. Dean
发明人： Narendra D. Joshi , Paul R. Angel , James M. Caldwell , Paul V. Heberling , Anthony J. Dean
IPC分类号： F23C7/00 , F23D17/00 , F23R3/14 , F23R3/36 , F02C1/00
CPC分类号： F23R3/36 , F23C7/004 , F23D17/002 , F23R3/14 , F23C2900/07001 , F23D2209/30
摘要： An air fuel mixer is disclosed having a mixing duct, a shroud surrounding the upstream end of the mixing duct in which a fuel manifold is provided in flow communication with a fuel supply and control means, a set of inner and outer counter-rotating swirlers adjacent the upstream end of the mixing duct for imparting swirl to an air stream, a hub separating the inner and outer annular swirlers to allow independent rotation of the air stream, and a centerbody located axially along and substantially the full length of the mixing duct. In order to inject one type of fuel into the mixing duct, fuel is supplied to the outer annular swirlers which include hollow vanes with internal cavities, wherein the internal cavities of the outer swirler vanes are in fluid communication with the fuel manifold in the shroud. The outer swirler vanes further include a plurality of fuel passages therethrough in flow communication with the internal cavities. A second fuel can be injected into the mixing duct by means of a plurality of orifices in the centerbody wall which are in flow communication with a fuel supply and control means. In this way, high pressure air from a compressor is injected into the mixing duct through the swirlers to form an intense shear region and fuel is injected into the mixing duct from the outer swirler vane passages and/or the centerbody orifices so that the high pressure air and the fuel is uniformly mixed therein so as to produce minimal formation of pollutants when a fuel/air mixture is exhausted out the downstream end of the mixing duct into the combustor and ignited.

5. 发明授权

US5675971A Dual fuel mixer for gas turbine combustor 失效
标题翻译：用于燃气轮机燃烧器的双燃料混合器
公开(公告)号：US5675971A
公开(公告)日：1997-10-14
申请号：US581813
申请日：1996-01-02
申请人： Paul R. Angel , James M. Caldwell , Paul V. Heberling , Anthony J. Dean , Narendra D. Joshi
发明人： Paul R. Angel , James M. Caldwell , Paul V. Heberling , Anthony J. Dean , Narendra D. Joshi
IPC分类号： F23R3/28 , F02C1/00 , F02G3/00
CPC分类号： F23R3/286 , F23D2900/14004
摘要： An air fuel mixer is disclosed having a mixing duct, a shroud surrounding the upstream end of the mixing duct in which a fuel manifold is provided in flow communication with a fuel supply and control means, a set of inner and outer counter-rotating swirlers adjacent the upstream end of the mixing duct for imparting swirl to an air stream, a hub separating the inner and outer annular swirlers to allow independent rotation of the air stream, and a centerbody located axially along and substantially the full length of the mixing duct. In order to inject one type of fuel into the mixing duct, fuel is supplied to the outer annular swirlers which include hollow vanes with internal cavities, wherein the internal cavities of the outer swirler vanes are in fluid communication with the fuel manifold in the shroud. The outer swirler vanes further include a plurality of fuel passages therethrough in flow communication with the internal cavities. A second fuel can be injected into the mixing duct by means of a plurality of orifices in the centerbody wall which are in flow communication with a fuel supply and control means. In this way, high pressure air from a compressor is injected into the mixing duct through the swirlers to form an intense shear region and fuel is injected into the mixing duct from the outer swirler vane passages and/or the centerbody orifices so that the high pressure air and the fuel is uniformly mixed therein so as to produce minimal formation of pollutants when a fuel/air mixture is exhausted out the downstream end of the mixing duct into the combustor and ignited.
摘要翻译：公开了一种空气燃料混合器，其具有混合管道，围绕混合管道的上游端的护罩，其中设置有与燃料供应和控制装置流动连通的燃料歧管，一组相邻的内部和外部反向旋转旋流器混合管道的上游端，用于向气流产生涡流;轮毂，分隔内外环形旋流器，以允许空气流的独立旋转;以及沿着混合管道的大致整个长度方向定位的中心体。为了将一种类型的燃料喷射到混合管道中，燃料被供应到外部环形旋流器，其包括具有内部空腔的中空叶片，其中外部旋流器叶片的内部空腔与护罩中的燃料歧管流体连通。外旋流器叶片还包括与内腔流动连通的多个通过其的燃料通道。第二燃料可以通过与燃料供应和控制装置流动连通的中心体壁中的多个喷嘴喷射到混合管道中。以这种方式，来自压缩机的高压空气通过旋流器喷射到混合管道中以形成强烈的剪切区域，并且燃料从外部旋流器叶片通道和/或中心体孔口喷射到混合管道中，使得高压空气和燃料均匀地混合在一起，以便当燃料/空气混合物从混合管道的下游端排出到燃烧器中并点燃时，产生最小的污染物形成。

6. 发明授权

US06983605B1 Methods and apparatus for reducing gas turbine engine emissions 有权
标题翻译：减少燃气轮机发动机排放的方法和装置
公开(公告)号：US06983605B1
公开(公告)日：2006-01-10
申请号：US09545554
申请日：2000-04-07
申请人： Richard B. Hook , John M. Davidson , Eric J. Kress , Jack W. Smith, Jr. , James W. Stegmaier , Paul V. Heberling , David B. Patterson
发明人： Richard B. Hook , John M. Davidson , Eric J. Kress , Jack W. Smith, Jr. , James W. Stegmaier , Paul V. Heberling , David B. Patterson
IPC分类号： F02C3/30
CPC分类号： F23L7/002 , F23L2900/07009 , F23R3/286
摘要： A gas turbine engine includes a combustor system including a lean premix combustor and a water delivery system. The combustor is operable with a fuel/air mixture equivalence ratio less than one and the water delivery system is configured to supply at least one of water or steam to the gas turbine engine such that either the water or the steam is injected into the combustor to control emissions generated by the combustor. As a result, nitrous oxide emissions for specified turbine operating power levels are lowered.
摘要翻译：燃气涡轮发动机包括包括贫预混燃烧器和输水系统的燃烧器系统。燃烧器可操作的燃料/空气混合物当量比小于1，并且水输送系统构造成将水或蒸汽中的至少一种供应到燃气涡轮发动机，使得水或蒸汽被注入到燃烧器中控制燃烧器产生的排放。因此，指定的涡轮机工作功率水平的一氧化二氮排放量会降低。

7. 发明授权

US5778676A Dual fuel mixer for gas turbine combustor 失效
标题翻译：用于燃气轮机燃烧器的双燃料混合器
公开(公告)号：US5778676A
公开(公告)日：1998-07-14
申请号：US581817
申请日：1996-01-02
申请人： Narendra D. Joshi , Paul R. Angel , James M. Caldwell , Paul V. Heberling , Anthony J. Dean
发明人： Narendra D. Joshi , Paul R. Angel , James M. Caldwell , Paul V. Heberling , Anthony J. Dean
IPC分类号： F23D11/10 , F23D17/00 , F23R3/14 , F23R3/36 , F02C1/00 , F02G3/00
CPC分类号： F23R3/14 , F23D11/101 , F23D17/002 , F23R3/36 , F23C2900/07001 , F23D2209/10 , F23D2209/30
摘要： An air fuel mixer is disclosed having a mixing duct, a shroud surrounding the upstream end of the mixing duct in which a fuel manifold is provided in flow communication with a fuel supply and control means, a set of inner and outer counter-rotating swirlers adjacent the upstream end of the mixing duct for imparting swirl to an air stream, a hub separating the inner and outer annular swirlers to allow independent rotation of the air stream, and a centerbody located axially along and substantially the full length of the mixing duct. In order to inject one type of fuel into the mixing duct, fuel is supplied to the outer annular swirlers which include hollow vanes with internal cavities, wherein the internal cavities of the outer swirler vanes are in fluid communication with the fuel manifold in the shroud. The outer swirler vanes further include a plurality of fuel passages therethrough in flow communication with the internal cavities. A second fuel can be injected into the mixing duct by means of a plurality of orifices in the centerbody wall which are in flow communication with a fuel supply and control means. In this way, high pressure air from a compressor is injected into the mixing duct through the swirlers to form an intense shear region and fuel is injected into the mixing duct from the outer swirler vane passages and/or the centerbody orifices so that the high pressure air and the fuel is uniformly mixed therein so as to produce minimal formation of poullutants when a fuel/air mixture is exhausted out the downstream end of the mixing duct into the combustor and ignited.
摘要翻译：公开了一种空气燃料混合器，其具有混合管道，围绕混合管道的上游端的护罩，其中设置有与燃料供应和控制装置流动连通的燃料歧管，一组相邻的内部和外部反向旋转旋流器混合管道的上游端，用于向气流产生涡流;轮毂，分隔内外环形旋流器，以允许空气流的独立旋转;以及沿着混合管道的大致整个长度方向定位的中心体。为了将一种类型的燃料喷射到混合管道中，燃料被供应到外部环形旋流器，其包括具有内部空腔的中空叶片，其中外部旋流器叶片的内部空腔与护罩中的燃料歧管流体连通。外旋流器叶片还包括与内腔流动连通的多个通过其的燃料通道。第二燃料可以通过与燃料供应和控制装置流动连通的中心体壁中的多个喷嘴喷射到混合管道中。以这种方式，来自压缩机的高压空气通过旋流器喷射到混合管道中以形成强烈的剪切区域，并且燃料从外部旋流器叶片通道和/或中心体孔口喷射到混合管道中，使得高压空气和燃料均匀地混合在一起，以便当燃料/空气混合物从混合管道的下游端排出到燃烧器中并点燃时，产生最小的起泡器的形成。

8. 发明授权

US5540056A Cyclonic prechamber with a centerbody for a gas turbine engine combustor 失效
标题翻译：具有用于燃气涡轮发动机燃烧器的中心体的旋风预燃室
公开(公告)号：US5540056A
公开(公告)日：1996-07-30
申请号：US399286
申请日：1995-03-06
申请人： Paul V. Heberling , Mark P. Kelsey , Willard J. Dodds
发明人： Paul V. Heberling , Mark P. Kelsey , Willard J. Dodds
IPC分类号： F23D11/36 , F23D11/44 , F23R3/12 , F23R3/14 , F23R3/32
CPC分类号： F23R3/12 , F23D11/36 , F23D11/441 , F23R3/14 , Y02T50/675
摘要： A cyclonic precombustion mixing chamber or prechamber has an axially extending annular cyclonic chamber to vaporize liquid fuel therein and a centerbody centrally disposed within. A fuel injection means introduces liquid fuel radially outward into the cyclonic chamber. The centerbody extends axially through an annular exit of the prechamber to define a throat and throat exit therebetween which is optimally designed for preventing backflash and autoignition. In one embodiment the diameter of the throat is sized to substantially match the diameter of the potential core.
摘要翻译：旋风预燃混合室或预燃室具有轴向延伸的环形旋流室，以使其中的液体燃料蒸发，并且集中设置在其中的中心体。燃料喷射装置将液体燃料径向向外引入旋风室。中心体轴向延伸通过预制室的环形出口，以在其间限定出喉部和喉部出口，其最佳设计用于防止反向闪光和自燃。在一个实施例中，喉部的直径的尺寸被设计成基本匹配电位芯的直径。

9. 发明授权

US4246757A Combustor including a cyclone prechamber and combustion process for gas turbines fired with liquid fuel 失效
标题翻译：燃烧器包括用液体燃料燃烧的燃气轮机的旋风预燃室和燃烧过程
公开(公告)号：US4246757A
公开(公告)日：1981-01-27
申请号：US24265
申请日：1979-03-27
申请人： Paul V. Heberling
发明人： Paul V. Heberling
IPC分类号： F23R3/28 , F23R3/14 , F23R3/30 , F02C7/22
CPC分类号： F23R3/30 , F23R3/14 , Y02T50/675
摘要： A combustor useful for combustion of initially liquid fuel to provide motive fluid for gas turbines is described. The combustor includes an air-swirling cyclonic prechamber having a wide-angle spray-cone liquid nozzle and opening to a downstream combustion chamber. The prechamber provides long residence time for liquid fuel being vaporized therein, short residence time for the resulting mixture of fuel vapor and air, and capability for minimal formation of nitrogen oxides.
摘要翻译：描述了用于燃烧初始液体燃料以提供用于燃气轮机的动力流体的燃烧器。燃烧器包括具有广角喷雾锥形液体喷嘴并且向下游燃烧室开口的空气旋转旋风预燃室。预燃室为液体燃料在其中蒸发提供长停留时间，所得到的燃料蒸气和空气混合物的停留时间短，以及氮氧化物形成最少的能力。

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