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。

公开(公告)号：US20070028618A1

公开(公告)日：2007-02-08

申请号：US11188598

申请日：2005-07-25

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

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

IPC分类号： F23R3/14

CPC分类号： F23R3/343 ,  F23D2209/30 ,  F23R3/14 ,  F23R3/286 ,  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 positioned between the pilot mixer and main mixer. The pilot mixer includes an annular pilot housing having a hollow interior and a pilot fuel nozzle mounted in the housing and adapted for dispensing droplets of fuel to the hollow interior of the pilot housing. The main mixer includes: a main housing surrounding the pilot housing and defining an annular cavity having an upstream end and a downstream end including an upstream wall, an outer wall and an inner wall; a plurality of fuel injection ports for introducing fuel into the cavity, with the fuel injection ports being circumferentially spaced at a designated axial location of the inner wall of the annular cavity; and a swirler arrangement including at least one swirler in flow communication with the annular cavity, the swirler being incorporated into the outer wall of the annular cavity and extending from an upstream end to a downstream end, wherein each swirler of the arrangement has a plurality of vanes for swirling air traveling through such swirler to mix air and the droplets of fuel dispensed by the fuel injection ports. The main housing further includes a first plurality of passages oriented to provide air jets in a substantially axial direction into the annular cavity and a second plurality of passages oriented to provide air jets in a substantially radial direction into the annular cavity

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。 先导式混合器包括环形导向壳体，其具有中空的内部和安装在壳体中的先导燃料喷嘴，适于将燃料液滴分配到飞行员舱的中空内部。 主混合器包括：围绕引导壳体并限定具有上游端和包括上游壁，外壁和内壁的下游端的环形空腔的主壳体; 多个燃料喷射口，其用于将燃料引入所述空腔中，所述燃料喷射口在所述环形腔的内壁的指定的轴向位置周向间隔开; 以及旋流器装置，其包括至少一个与所述环形腔流动连通的旋流器，所述旋流器被结合到所述环形空腔的外壁中并且从上游端延伸到下游端，其中所述装置的每个旋流器具有多个 用于旋转的涡流的叶片通过这种旋流器移动以混合空气和由燃料喷射端口分配的燃料的液滴。 主壳体还包括第一多个通道，其被定向成将大致轴向的空气射流提供到环形空腔中，以及第二多个通道，其定向成将空气射流基本上沿径向提供到环形空腔

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：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：US20070028617A1

公开(公告)日：2007-02-08

申请号：US11188470

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： F23R3/286 ,  F23D2209/30 ,  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 positioned between the pilot mixer and main mixer. The pilot mixer includes an annular pilot housing having a hollow interior and a pilot fuel nozzle mounted in the housing and adapted for dispensing droplets of fuel to 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 for introducing fuel into the cavity; a post member associated with and extending from each fuel injection port to an inner surface of said annular cavity, the post member including an inner passage therethrough in flow communication with the fuel injection port; a passage surrounding each post member, wherein air is provided therefrom to envelop fuel injected into the annular cavity; and, a swirler arrangement including at least one swirler positioned upstream from the fuel injection ports, wherein each swirler of the arrangement has a plurality of vanes for swirling air traveling through such swirler to mix air and the droplets of fuel dispensed by the fuel injection ports. The air through the passages is either injected substantially straight through or swirled a predetermined amount.

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。 先导式混合器包括环形导向壳体，其具有中空的内部和安装在壳体中的先导燃料喷嘴，适于将燃料液滴分配到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的主壳体; 多个用于将燃料引入所述空腔的燃料喷射口; 与每个燃料喷射口相关联并且从每个燃料喷射口延伸到所述环形空腔的内表面的柱构件，所述柱构件包括与所述燃料喷射口流动连通的通过其的内部通道; 围绕每个柱构件的通道，其中从其中提供空气以包围注入到所述环形空腔中的燃料; 以及旋流器装置，其包括位于燃料喷射口的上游的至少一个旋流器，其中该装置的每个旋流器具有多个叶片，用于旋转通过该旋流器的空气旋转以混合空气和燃料喷射端口分配的燃料液滴 。 通过通道的空气基本上直接注入或旋转预定量。

公开(公告)号：US20050103020A1

公开(公告)日：2005-05-19

申请号：US10929805

申请日：2004-08-30

申请人： Alfred Mancini ,  Michael Vermeersch ,  Duane Thomsen ,  Allen Danis ,  James Cooper ,  Steven Lohmueller ,  Hukam Mongia

发明人： Alfred Mancini ,  Michael Vermeersch ,  Duane Thomsen ,  Allen Danis ,  James Cooper ,  Steven Lohmueller ,  Hukam Mongia

IPC分类号： F23R3/14 ,  F23R3/16 ,  F23R3/28

CPC分类号： F23R3/286 ,  F23D2900/00016 ,  F23R3/16

摘要： A method for operating a gas turbine engine facilitates reducing an amount of emissions from a combustor. The combustor includes a mixer assembly including a pilot mixer, a main mixer, and a centerbody that extends therebetween. The pilot mixer includes a pilot fuel nozzle and a plurality of axial swirlers. The main mixer includes a main swirler and a plurality of fuel injection ports. The method comprises injecting fuel into the combustor through the pilot mixer, such that the fuel is discharged downstream from the pilot mixer axial swirlers, and directing flow exiting the pilot mixer with a lip extending from the centerbody into a pilot flame zone downstream from said pilot mixer.

公开(公告)号：US20070137207A1

公开(公告)日：2007-06-21

申请号：US11312728

申请日：2005-12-20

申请人： Alfred Mancini ,  Hukam Mongia

发明人： Alfred Mancini ,  Hukam Mongia

IPC分类号： F23R3/30

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

摘要： A mixer assembly for a gas turbine engine, including: a primary fuel injector having a central axis for injecting a primary fuel spray into a primary air stream, wherein fuel is provided at a desired rate and droplets of the fuel spray are within a desired size range; a secondary fuel injector positioned radially outwardly of the primary fuel injector for injecting a secondary fuel spray into a secondary air stream spaced radially outwardly of and surrounding the primary air stream; and, a primary air jet positioned between the primary fuel injector and the secondary fuel injector to direct a portion of an incoming air stream between the primary air stream and the secondary air stream.

摘要翻译： 一种用于燃气涡轮发动机的混合器组件，包括：主燃料喷射器，其具有用于将初级燃料喷雾喷射到一次空气流中的中心轴线，其中以期望的速率提供燃料，并且燃料喷雾的液滴在期望的尺寸内 范围; 位于所述主燃料喷射器径向外侧的二次燃料喷射器，用于将二次燃料喷射喷射到沿所述一次空气流径向向外并围绕所述主气流的二次空气流中; 以及定位在主燃料喷射器和次燃料喷射器之间的一次空气喷射器，以将一部分进气流引导到一次空气流和二次空气流之间。