公开(公告)号：US20080229753A1

公开(公告)日：2008-09-25

申请号：US11689759

申请日：2007-03-22

申请人： Shui-Chi Li ,  Michael Louis Vermeersch ,  Zhong-Tao Dai ,  Timothy James Held ,  Mark Anthony Mueller

发明人： Shui-Chi Li ,  Michael Louis Vermeersch ,  Zhong-Tao Dai ,  Timothy James Held ,  Mark Anthony Mueller

IPC分类号： F02C3/04

CPC分类号： F23R3/343 ,  F23R3/14 ,  F23R3/26

摘要： A method for operating a gas turbine engine including a compressor and a combustor is provided. The method comprises channeling between about 0% to about 8% of the total airflow discharged from a compressor towards a pilot swirler coupled within the burner, wherein the burner includes a main swirler and an annular centerbody extending between the pilot and main swirlers, injecting a portion of the total fuel flow supplied to the burner through a plurality of apertures defined in a hollow pilot centerbody coupled within the pilot swirler, channeling the remaining airflow discharged from the compressor towards the main swirler, and injecting the remaining fuel flow supplied to the burner through at least one main swirler vane coupled within the main swirler, such that the portion of fuel is pre-mixed with a portion of the total airflow.

摘要翻译： 提供了一种用于操作包括压缩机和燃烧器的燃气涡轮发动机的方法。 该方法包括将从压缩机排出的总气流的约0％至约8％引导至连接在燃烧器内的先导式旋流器，其中燃烧器包括主旋流器和在飞行员和主旋流器之间延伸的环形中心体， 通过被连接在先导式旋流器内的中空先导中心体中限定的多个孔口供应到燃烧器的总燃料流量的一部分，将从压缩机排出的剩余气流引导到主旋流器，以及喷射供应到燃烧器的剩余燃料流 通过联接在主旋流器内的至少一个主旋流器叶片，使得燃料的一部分与总气流的一部分预混合。

公开(公告)号：US07905093B2

公开(公告)日：2011-03-15

申请号：US11689759

申请日：2007-03-22

申请人： Shui-Chi Li ,  Michael Louis Vermeersch ,  Zhong-Tao Dai ,  Timothy James Held ,  Mark Anthony Mueller

发明人： Shui-Chi Li ,  Michael Louis Vermeersch ,  Zhong-Tao Dai ,  Timothy James Held ,  Mark Anthony Mueller

IPC分类号： F02C1/00

CPC分类号： F23R3/343 ,  F23R3/14 ,  F23R3/26

摘要： A method for operating a gas turbine engine including a compressor and a combustor is provided. The method comprises channeling between about 0% to about 8% of the total airflow discharged from a compressor towards a pilot swirler coupled within the burner, wherein the burner includes a main swirler and an annular centerbody extending between the pilot and main swirlers, injecting a portion of the total fuel flow supplied to the burner through a plurality of apertures defined in a hollow pilot centerbody coupled within the pilot swirler, channeling the remaining airflow discharged from the compressor towards the main swirler, and injecting the remaining fuel flow supplied to the burner through at least one main swirler vane coupled within the main swirler, such that the portion of fuel is pre-mixed with a portion of the total airflow.

摘要翻译： 提供了一种用于操作包括压缩机和燃烧器的燃气涡轮发动机的方法。 该方法包括将从压缩机排出的总气流的约0％至约8％引导至连接在燃烧器内的先导式旋流器，其中燃烧器包括主旋流器和在飞行员和主旋流器之间延伸的环形中心体， 通过被连接在先导式旋流器内的中空先导中心体中限定的多个孔口供应到燃烧器的总燃料流量的一部分，将从压缩机排出的剩余气流引导到主旋流器，以及喷射供应到燃烧器的剩余燃料流 通过联接在主旋流器内的至少一个主旋流器叶片，使得燃料的一部分与总气流的一部分预混合。

公开(公告)号：US20100162713A1

公开(公告)日：2010-07-01

申请号：US12347165

申请日：2008-12-31

申请人： Shui-Chi Li ,  Mark Anthony Mueller ,  Michael Louis Vermeersch ,  Timothy James Held

发明人： Shui-Chi Li ,  Mark Anthony Mueller ,  Michael Louis Vermeersch ,  Timothy James Held

IPC分类号： F02C1/00

CPC分类号： F23R3/286 ,  F23R3/14 ,  F23R3/20 ,  F23R3/343 ,  F23R2900/03044 ,  Y02T50/675

摘要： A combustor swirl cup includes coaxial inner and outer swirlers separated by a tubular centerbody. The centerbody includes a bypass inlet surrounding the inner swirler and diverges aft along a perforate inner nozzle to terminate at an annular flameholder. An impingement ring is spaced forward from the flameholder in flow communication with the bypass inlet for receiving cooling air therefrom to impingement cool the flameholder.

摘要翻译： 燃烧器旋流杯包括由管状中心体分开的同心的内旋流器和外旋流器。 中心体包括围绕内旋流器的旁路入口，并沿着穿孔内喷嘴向后分叉，以终止于环形火焰稳定器。 冲击环与火焰稳压器间隔开，与旁路入口流动连通，以从其中接收冷却空气，以冲击冷却火焰稳定器。

公开(公告)号：US08281597B2

公开(公告)日：2012-10-09

申请号：US12347165

申请日：2008-12-31

申请人： Shui-Chi Li ,  Mark Anthony Mueller ,  Michael Louis Vermeersch ,  Timothy James Held

发明人： Shui-Chi Li ,  Mark Anthony Mueller ,  Michael Louis Vermeersch ,  Timothy James Held

IPC分类号： F02C1/00

CPC分类号： F23R3/286 ,  F23R3/14 ,  F23R3/20 ,  F23R3/343 ,  F23R2900/03044 ,  Y02T50/675

摘要： A combustor swirl cup includes coaxial inner and outer swirlers separated by a tubular centerbody. The centerbody includes a bypass inlet surrounding the inner swirler and diverges aft along a perforate inner nozzle to terminate at an annular flameholder. An impingement ring is spaced forward from the flameholder in flow communication with the bypass inlet for receiving cooling air therefrom to impingement cool the flameholder.

摘要翻译： 燃烧器旋流杯包括由管状中心体分开的同心的内旋流器和外旋流器。 中心体包括围绕内旋流器的旁路入口，并沿着穿孔内喷嘴向后分叉，以终止于环形火焰稳定器。 冲击环与火焰稳压器间隔开，与旁路入口流动连通，以从其中接收冷却空气，以冲击冷却火焰稳定器。

公开(公告)号：US20070017224A1

公开(公告)日：2007-01-25

申请号：US11188595

申请日：2005-07-25

申请人： Shui-Chi Li ,  Shih-Yang Hsieh ,  George Hsiao ,  Hukam Mongia

发明人： Shui-Chi Li ,  Shih-Yang Hsieh ,  George Hsiao ,  Hukam Mongia

IPC分类号： F23R3/14

CPC分类号： F23R3/14 ,  F23R3/286 ,  F23R3/343 ,  Y02T50/675

摘要： A swirler arrangement for a mixing assembly of a gas turbine engine combustor, where the swirler arrangement has a centerline axis therethrough, including: a swirler housing including an outer radial wall and an upstream wall; a first plurality of vanes incorporated into the outer radial wall, wherein the first plurality of vanes are oriented at a first angle with respect to an axis through the outer radial wall; and, a second plurality of vanes incorporated into the outer radial wall, wherein the second plurality of vanes are oriented at a second angle with respect to the through the outer radial wall. A first type of passage is defined between adjacent first and second vanes having a first configuration and a second type of passage is defined between adjacent first and second vanes having a second configuration so that air flowing through the swirler arrangement is swirled in a desirable manner. The axis through the outer radial wall may be oriented either substantially radially to the centerline axis or at an acute angle to the centerline axis.

摘要翻译： 一种用于燃气涡轮发动机燃烧器的混合组件的旋流器装置，其中旋流器装置具有穿过其的中心线轴线，包括：包括外径向壁和上游壁的旋流器壳体; 并入所述外径向壁中的第一多个叶片，其中所述第一多个叶片相对于穿过所述外径向壁的轴线以第一角度定向; 以及并入到所述外径向壁中的第二多个叶片，其中所述第二多个叶片相对于所述外径向壁以第二角度定向。 第一类型的通道被限定在具有第一构造的相邻的第一和第二叶片之间，并且第二类型的通道被限定在具有第二构造的相邻的第一和第二叶片之间，使得流过旋流器装置的空气以期望的方式旋转。 穿过外部径向壁的轴线可以大致径向地定向到中心线轴线或者与中心线轴线成锐角。

公开(公告)号：US07762073B2

公开(公告)日：2010-07-27

申请号：US11365428

申请日：2006-03-01

申请人： Shui-Chi Li ,  Shih-Yang Hsieh ,  George Chia-Chun Hsiao ,  Hukam Chand Mongia

发明人： Shui-Chi Li ,  Shih-Yang Hsieh ,  George Chia-Chun Hsiao ,  Hukam Chand Mongia

IPC分类号： F02C1/00 ,  F02G3/00

CPC分类号： F23R3/286 ,  F23R3/14 ,  F23R3/343 ,  Y02T50/675

摘要： A mixer assembly for use in a combustion chamber of a gas turbine engine includes a pilot mixer, a main mixer, and a fuel manifold. The pilot mixer includes: an annular pilot housing having a hollow interior, a primary fuel injector mounted in the pilot housing, a plurality of axial swirlers positioned upstream from the primary fuel injector, and a plurality of secondary fuel injection ports for introducing fuel into the hollow interior of the pilot housing. The main mixer includes: a main housing surrounding the pilot housing and defining an annular cavity, a plurality of fuel injection ports, and at least one swirler positioned upstream from the plurality of fuel injection ports. The fuel manifold is in flow communication with the plurality of secondary fuel injection ports in the pilot mixer and the plurality of fuel injection ports in the main mixer.

摘要翻译： 用于燃气涡轮发动机的燃烧室的混合器组件包括先导式混合器，主混合器和燃料歧管。 先导式混合器包括：环形导向壳体，其具有中空内部，安装在先导壳体中的主燃料喷射器，位于主燃料喷射器上游的多个轴向旋流器，以及多个二次燃料喷射端口，用于将燃料引入 飞行员舱的中空内部。 主混合器包括：围绕引导壳体并限定环形空腔，多个燃料喷射端口和位于多个燃料喷射端口的上游的至少一个旋流器的主壳体。 燃料歧管与先导混合器中的多个二次燃料喷射口和主混合器中的多个燃料喷射口流动连通。

公开(公告)号：US20070028624A1

公开(公告)日：2007-02-08

申请号：US11188596

申请日：2005-07-25

申请人： Shih-Yang Hsieh ,  George Hsiao ,  Shui-Chi Li ,  Hukam Mongia

发明人： Shih-Yang Hsieh ,  George Hsiao ,  Shui-Chi Li ,  Hukam Mongia

IPC分类号： F23R3/14

CPC分类号： F23R3/14 ,  F23R3/286 ,  F23R3/343 ,  Y02T50/675

摘要： A mixer assembly for use in a combustor of a gas turbine engine, including a pilot mixer, a main mixer, and a fuel manifold positioned between the pilot mixer and the main mixer. The pilot mixer further includes an annular pilot housing having a hollow interior and a pilot fuel nozzle mounted in the pilot housing and adapted for dispensing droplets of fuel to the hollow interior of the pilot housing. The main mixer further includes a main housing surrounding the pilot housing and defining an annular cavity, a plurality of fuel injection ports for introducing fuel into the cavity, and a swirler arrangement including at least three swirlers positioned upstream from the plurality of fuel injection ports, wherein each swirler of the swirler arrangement has a plurality of vanes for swirling air traveling through the respective swirler to mix air and the droplets of fuel dispensed by the fuel injection ports. The swirlers are oriented substantially radially to a centerline axis through the mixer assembly or at an acute angle to the centerline axis through the mixer assembly. Alternatively, at least two swirlers are included substantially parallel to the centerline axis through the mixer assembly along with one or more radial or conical swirlers. In another alternative, the swirler arrangement includes a first swirler oriented substantially parallel to a centerline axis through the mixer assembly, a second swirler oriented at an acute angle to the centerline axis through the mixer assembly, and a third swirler oriented substantially radially to the centerline axis through the mixer assembly.

摘要翻译： 一种用于燃气涡轮发动机的燃烧器的混合器组件，包括先导混合器，主混合器和位于先导混合器和主混合器之间的燃料歧管。 先导式混合器还包括具有中空内部的环形导向壳体和安装在导向壳体中的导向燃料喷嘴，并适于将燃料液滴分配到导向壳体的中空内部。 主混合器还包括围绕引导壳体并限定环形空腔的主壳体，用于将燃料引入空腔的多个燃料喷射端口以及包括位于多个燃料喷射端口上游的至少三个旋流器的旋流器装置， 其中所述旋流器装置的每个旋流器具有多个叶片，用于旋转通过相应的旋流器的旋转空气以混合空气和由燃料喷射端口分配的燃料的液滴。 旋流器通过混合器组件基本径向地定向到中心线轴线，或者通过混合器组件与中心线轴线成锐角。 或者，包括至少两个旋流器，其基本上平行于通过混合器组件的中心线轴线以及一个或多个径向或圆锥形旋流器。 在另一替代方案中，旋流器装置包括基本上平行于通过混合器组件的中心线轴线定向的第一旋流器，通过混合器组件与中心线轴线成锐角定向的第二旋流器，以及基本上径向定向到中心线的第三旋流器 轴通过混合器组件。

公开(公告)号：US08607575B2

公开(公告)日：2013-12-17

申请号：US12830835

申请日：2010-07-06

申请人： William Joseph Myers, Jr. ,  Alfred Albert Mancini ,  George Chia-Chun Hsiao ,  Shui-Chi Li ,  Shih-Yang Hsieh ,  Hukam Chand Mongia

发明人： William Joseph Myers, Jr. ,  Alfred Albert Mancini ,  George Chia-Chun Hsiao ,  Shui-Chi Li ,  Shih-Yang Hsieh ,  Hukam Chand Mongia

IPC分类号： F02C9/00

CPC分类号： F02C9/28 ,  F23R3/286 ,  F23R3/346 ,  F23R2900/00013

摘要： A method for actively controlling fuel flow from a fuel pump to a mixer assembly of a gas turbine engine combustor, where the mixer assembly includes a pilot mixer and a main mixer. The pilot mixer further includes an annular pilot housing having a hollow interior, a primary fuel injector mounted in the pilot housing and adapted for dispensing droplets of fuel to the hollow interior of the pilot housing, a plurality of axial swirlers positioned upstream from the primary fuel injector. The fuel flow control apparatus further includes: at least one sensor for detecting dynamic pressure in the combustor; a fuel nozzle; and, a system for controlling fuel flow supplied by the fuel nozzle through the valves. The fuel nozzle includes: a feed strip with a plurality of circuits for providing fuel to the pilot mixer and the main mixer; and, a plurality of valves associated with the fuel nozzle and in flow communication with the feed strip thereof. The control system activates the valves in accordance with signals received from the pressure sensor.

摘要翻译： 一种用于主动地控制从燃料泵到燃气涡轮发动机燃烧器的混合器组件的燃料流的方法，其中混合器组件包括先导式混合器和主混合器。 先导式混合器还包括具有中空内部的环形导向壳体，安装在导向壳体中并适于将燃料液滴分配到导向壳体的中空内部的主燃料喷射器，多个轴向旋流器，其位于主燃料 注射器。 燃料流量控制装置还包括：用于检测燃烧器中的动态压力的至少一个传感器; 燃料喷嘴; 以及用于控制由燃料喷嘴通过阀提供的燃料流量的系统。 燃料喷嘴包括：具有用于向先导混合器和主混合器提供燃料的多个回路的进料条; 以及与燃料喷嘴相关联并与其进给条流动连通的多个阀。 控制系统根据从压力传感器接收的信号激活阀门。

公开(公告)号：US07565803B2

公开(公告)日：2009-07-28

申请号：US11188595

申请日：2005-07-25

申请人： Shui-Chi Li ,  Shih-Yang Hsieh ,  George Chia-Chun Hsiao ,  Hukam Chand Mongia

发明人： Shui-Chi Li ,  Shih-Yang Hsieh ,  George Chia-Chun Hsiao ,  Hukam Chand Mongia

IPC分类号： F02C1/00

CPC分类号： F23R3/14 ,  F23R3/286 ,  F23R3/343 ,  Y02T50/675

摘要： A swirler arrangement for a mixing assembly of a gas turbine engine combustor, where the swirler arrangement has a centerline axis therethrough, including: a swirler housing including an outer radial wall and an upstream wall; a first plurality of vanes incorporated into the outer radial wall, wherein the first plurality of vanes are oriented at a first angle with respect to an axis through the outer radial wall; and, a second plurality of vanes incorporated into the outer radial wall, wherein the second plurality of vanes are oriented at a second angle with respect to the through the outer radial wall. A first type of passage is defined between adjacent first and second vanes having a first configuration and a second type of passage is defined between adjacent first and second vanes having a second configuration so that air flowing through the swirler arrangement is swirled in a desirable manner. The axis through the outer radial wall may be oriented either substantially radially to the centerline axis or at an acute angle to the centerline axis.

摘要翻译： 一种用于燃气涡轮发动机燃烧器的混合组件的旋流器装置，其中旋流器装置具有穿过其的中心线轴线，包括：包括外径向壁和上游壁的旋流器壳体; 并入所述外径向壁中的第一多个叶片，其中所述第一多个叶片相对于穿过所述外径向壁的轴线以第一角度定向; 以及并入到所述外径向壁中的第二多个叶片，其中所述第二多个叶片相对于所述外径向壁以第二角度定向。 第一类型的通道被限定在具有第一构造的相邻的第一和第二叶片之间，并且第二类型的通道被限定在具有第二构造的相邻的第一和第二叶片之间，使得流过旋流器装置的空气以期望的方式旋转。 穿过外部径向壁的轴线可以大致径向地定向到中心线轴线或者与中心线轴线成锐角。

公开(公告)号：US20070028595A1

公开(公告)日：2007-02-08

申请号：US11188483

申请日：2005-07-25

申请人： Hukam Mongia ,  George Hsiao ,  Shui-Chi Li ,  Shih-Yang Hsieh ,  Alfred Mancini ,  David Burrus ,  Marie McMasters ,  Duane Thomsen

发明人： Hukam Mongia ,  George Hsiao ,  Shui-Chi Li ,  Shih-Yang Hsieh ,  Alfred Mancini ,  David Burrus ,  Marie McMasters ,  Duane Thomsen

IPC分类号： F02K3/04 ,  F23R3/14

CPC分类号： F02K3/04 ,  F05D2270/082 ,  F23R3/06 ,  F23R3/14 ,  F23R3/286 ,  F23R3/343 ,  Y02T50/675 ,  Y02T50/677

摘要： A gas turbine engine having a longitudinal centerline axis therethrough, including a fan section at a forward end of the gas turbine engine for producing a first compressed air flow; a first compressor positioned downstream of the fan section and in flow communication with at least a portion of the first compressed air flow, wherein the first compressor produces a second compressed air flow having a designated pressure; a combustor positioned downstream of the first compressor and in flow communication with second compressed air flow, wherein the combustor produces combustion products from a mixture of fuel and air; a first turbine positioned downstream of the combustor and in flow communication with combustion products, wherein the first turbine powers the first compressor by means of a first rotatable drive shaft connected therebetween; and, a second turbine positioned downstream of the first turbine and in flow communication with the combustion products exiting the first turbine, wherein the second turbine powers the fan section by means of a second drive shaft connected therebetween. The gas turbine engine produces no more than a predetermined amount of emissions during an operating cycle.

摘要翻译： 一种燃气涡轮发动机，其具有穿过其的纵向中心线轴线，包括在所述燃气涡轮发动机的前端处的风扇部分，用于产生第一压缩空气流; 第一压缩机，其位于所述风扇部分的下游并且与所述第一压缩空气流的至少一部分流动连通，其中所述第一压缩机产生具有指定压力的第二压缩空气流; 位于所述第一压缩机下游并与所述第二压缩空气流流动连通的燃烧器，其中所述燃烧器从燃料和空气的混合物产生燃烧产物; 位于燃烧器下游并与燃烧产物流动的第一涡轮机，其中第一涡轮机通过连接在其间的第一可旋转驱动轴来驱动第一压缩机; 以及位于第一涡轮机下游并与离开第一涡轮机的燃烧产物流动连通的第二涡轮机，其中第二涡轮机通过连接在其间的第二驱动轴为风扇部分供电。 燃气涡轮发动机在操作循环期间产生不超过预定量的排放。