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：US20120151930A1

公开(公告)日：2012-06-21

申请号：US12971597

申请日：2010-12-17

申请人： Nayan Vinodbhai Patel ,  Michael Anthony Benjamin ,  Duane Douglas Thomsen ,  Alfred Albert Mancini

发明人： Nayan Vinodbhai Patel ,  Michael Anthony Benjamin ,  Duane Douglas Thomsen ,  Alfred Albert Mancini

IPC分类号： F02C7/22

CPC分类号： F23R3/283 ,  F23D11/383 ,  F23D11/386 ,  F23R3/286 ,  F23R3/36 ,  F23R2900/00004 ,  F23R2900/03042 ,  F23R2900/03044 ,  Y02T50/675

摘要： A pilot fuel injector tip includes concentric primary and secondary pilot fuel nozzles having a circular primary exit axially aft and downstream of an annular secondary exit respectively. A fuel nozzle assembly includes a pilot swirler flowpath section having an annular inwardly tapering conical flowpath section surrounding primary and secondary exits. An inwardly tapering conical wall section radially inwardly bounding flowpath section defines a conical surface. Exits are located at or axially forward or upstream of the conical surface. An annular secondary fuel supply passage in secondary pilot fuel nozzle includes a secondary fuel swirler with an array of helical spin slots that may have rectangular cross sections. A chamfered leading edge of an annular wall section disposed between an outer pilot swirler and an inlet to an injector cooling flowpath surrounding the second pilot swirler includes a radially inwardly facing conical chamfered surface for deflecting dirt from cooling flowpath.

摘要翻译： 先导燃料喷射器尖端包括同心的主要和次要的先导燃料喷嘴，其具有分别在环形二次出口的轴向后部和下游的圆形主出口。 燃料喷嘴组件包括具有包围主出口和次出口的环形向内渐缩的锥形流路部分的先导旋流器流路部分。 向内渐缩的锥形壁部分径向向内包围流动路径部分限定了锥形表面。 出口位于锥形表面的或轴向向前或上游。 次级引燃燃料喷嘴中的环形二次燃料供应通道包括具有矩形横截面的螺旋旋转槽阵列的二次燃料旋流器。 设置在外先导式旋流器和围绕第二先导式旋流器的喷射器冷却流路的入口之间的环形壁部分的倒角前缘包括径向向内的锥形倒角表面，用于使污物从冷却流动路径偏转。

公开(公告)号：US07311979B2

公开(公告)日：2007-12-25

申请号：US10711403

申请日：2004-09-16

申请人： Alfred Albert Mancini ,  John Frederick Ackerman ,  Kevin Richard Leamy ,  William Randolph Stowell

发明人： Alfred Albert Mancini ,  John Frederick Ackerman ,  Kevin Richard Leamy ,  William Randolph Stowell

IPC分类号： B32B15/04 ,  B32B18/00

CPC分类号： C23C28/345 ,  B01J19/0026 ,  B01J19/02 ,  B01J2219/0218 ,  B01J2219/0236 ,  B01J2219/0286 ,  C23C16/18 ,  C23C16/40 ,  C23C28/322 ,  C23C28/3455 ,  Y10T428/12611 ,  Y10T428/24975 ,  Y10T428/265

摘要： A coating system and method for reducing the tendency for hydrocarbon fluids, such as fuels and oils, to form carbonaceous deposits that adhere to a wall of a containment article. Of particular concern are carbonaceous deposits that form at temperatures below about 650° F. (about 345° C.). The coating system combines an outermost layer of platinum with a ceramic barrier layer. The coating system significantly reduces the formation of carbonaceous deposits and the adhesion of such deposits. To further reduce wall and hydrocarbon fluid temperatures and formation of carbonaceous deposits, the coating system is preferably applied to the surface of the wall wetted by the fluid, as well as the opposite surface of the wall exposed to a surrounding environment. The outermost layers serve as radiation shields to reduce heat transfer from the surrounding environment to the wall, and from the wall to the hydrocarbon fluid.

摘要翻译： 用于降低烃流体（例如燃料和油）倾向于形成附着在容纳物品的壁上的碳质沉积物的涂料体系和方法。 特别令人关注的是在低于约650°F（约345℃）下形成的碳质沉积物。 涂层系统将最外层的铂与陶瓷阻挡层相结合。 涂层体系显着减少了碳质沉积物的形成和这些沉积物的粘附。 为了进一步减少壁和烃流体温度和形成碳质沉积物，优选将涂层系统施加到被流体润湿的壁的表面以及暴露于周围环境的壁的相对表面上。 最外层用作辐射屏蔽，以减少从周围环境到壁以及从壁到烃流体的热传递。

公开(公告)号：US07036302B2

公开(公告)日：2006-05-02

申请号：US10801439

申请日：2004-03-15

申请人： William Joseph Myers Jr. ,  Thomas Vander Ng ,  Alfred Albert Mancini ,  James Neil Cooper

发明人： William Joseph Myers Jr. ,  Thomas Vander Ng ,  Alfred Albert Mancini ,  James Neil Cooper

IPC分类号： F02C7/232

CPC分类号： F23R3/343

摘要： A multi-staged gas turbine engine fuel supply system includes a plurality of fuel injectors and at least first and second staged fuel injection circuits in each of the fuel injectors. Each of the first and second staged fuel injection circuits includes first and second fuel injection points and at least first and second fuel nozzle valves operable to open at different first and second crack open pressures and controllably connected to the first and second staged fuel injection circuits, respectively. A single fuel supply manifold is connected to all of the fuel nozzle valves. A single fuel signal manifold is controllably connected to all of the first and second fuel nozzle valves. The fuel injector may have a valve housing with one of the first fuel nozzle valves and one of the second fuel nozzle valves contained therein.

摘要翻译： 多级燃气轮机发动机燃料供给系统包括多个燃料喷射器和每个燃料喷射器中的至少第一和第二分段燃料喷射回路。 第一和第二阶段燃料喷射回路中的每一个包括第一和第二燃料喷射点，并且至少第一和第二燃料喷嘴阀可操作以在不同的第一和第二裂纹开启压力下打开并且可控地连接到第一和第二分段燃料喷射回路， 分别。 单个燃料供应歧管连接到所有燃料喷嘴阀。 单个燃料信号歧管可控地连接到所有第一和第二燃料喷嘴阀。 燃料喷射器可以具有阀壳体，其中包含第一燃料喷嘴阀中的一个并且其中包含一个第二燃料喷嘴阀。

公开(公告)号：US08726668B2

公开(公告)日：2014-05-20

申请号：US12971597

申请日：2010-12-17

申请人： Nayan Vinodbhai Patel ,  Michael Anthony Benjamin ,  Duane Douglas Thomsen ,  Alfred Albert Mancini

发明人： Nayan Vinodbhai Patel ,  Michael Anthony Benjamin ,  Duane Douglas Thomsen ,  Alfred Albert Mancini

IPC分类号： F02C1/00

CPC分类号： F23R3/283 ,  F23D11/383 ,  F23D11/386 ,  F23R3/286 ,  F23R3/36 ,  F23R2900/00004 ,  F23R2900/03042 ,  F23R2900/03044 ,  Y02T50/675

摘要： A pilot fuel injector tip includes concentric primary and secondary pilot fuel nozzles having a circular primary exit axially aft and downstream of an annular secondary exit respectively. A fuel nozzle assembly includes a pilot swirler flowpath section having an annular inwardly tapering conical flowpath section surrounding primary and secondary exits. An inwardly tapering conical wall section radially inwardly bounding flowpath section defines a conical surface. Exits are located at or axially forward or upstream of the conical surface. An annular secondary fuel supply passage in secondary pilot fuel nozzle includes a secondary fuel swirler with an array of helical spin slots that may have rectangular cross sections. A chamfered leading edge of an annular wall section disposed between an outer pilot swirler and an inlet to an injector cooling flowpath surrounding the second pilot swirler includes a radially inwardly facing conical chamfered surface for deflecting dirt from cooling flowpath.

摘要翻译： 先导燃料喷射器尖端包括同心的主要和次要的先导燃料喷嘴，其具有分别在环形二次出口的轴向后部和下游的圆形主出口。 燃料喷嘴组件包括具有包围主出口和次出口的环形向内渐缩的锥形流路部分的先导旋流器流路部分。 向内渐缩的锥形壁部分径向向内包围流动路径部分限定了锥形表面。 出口位于锥形表面的或轴向向前或上游。 次级引燃燃料喷嘴中的环形二次燃料供应通道包括具有矩形横截面的螺旋旋转槽阵列的二次燃料旋流器。 设置在外先导式旋流器和围绕第二先导式旋流器的喷射器冷却流路的入口之间的环形壁部分的倒角前缘包括径向向内的锥形倒角表面，用于使污物从冷却流动路径偏转。

公开(公告)号：US08387391B2

公开(公告)日：2013-03-05

申请号：US12971676

申请日：2010-12-17

申请人： Nayan Vinodbhai Patel ,  Michael Anthony Benjamin ,  Duane Douglas Thomsen ,  Alfred Albert Mancini

发明人： Nayan Vinodbhai Patel ,  Michael Anthony Benjamin ,  Duane Douglas Thomsen ,  Alfred Albert Mancini

IPC分类号： F02C1/00

CPC分类号： F23R3/28 ,  F23R3/34 ,  F23R3/60

摘要： A gas turbine engine fuel nozzle assembly includes a pilot fuel injector tip substantially centered about a centerline axis in an annular pilot inlet to a pilot mixer. A cross over arm extends across inlet to tip. Arm includes an arm fairing surrounding at least one fuel transfer tube to tip. A pilot nose cap is at an upstream end of tip. At least one of the cross over arm and the pilot nose cap includes a rounded forebody followed by a straight afterbody. Rounded forebody of pilot nose cap includes a substantially rounded dome extending forwardly from a rounded nose base and straight afterbody includes a substantially cylindrical nose afterbody parallel to a pilot nose centerline normal to nose base. An arm fairing surrounding fuel transfer tubes to tip includes rounded leading and trailing edges and a rectangular middle section therebetween having flat first and second sides.

摘要翻译： 燃气涡轮发动机燃料喷嘴组件包括引导燃料喷射器尖端，其基本上以中心线轴线为中心，位于环形先导进口到先导混合器中。 横跨臂跨越入口到尖端。 臂包括围绕至少一个燃料传输管的手臂整流装置。 先导鼻帽位于尖端的上游端。 交叉臂和先导鼻帽中的至少一个包括圆形的前身，后跟一个直的后身。 飞行员鼻盖的圆形前身包括从圆形鼻基部向前延伸的大致圆形的圆顶，并且直的后身体包括平行于与鼻底基准面的导向鼻中心线平行的基本上圆柱形的鼻后体。 围绕燃料转移管至顶部的臂整流罩包括圆形的前缘和后缘以及其间具有平坦的第一和第二侧的矩形中间部分。

公开(公告)号：US20120151929A1

公开(公告)日：2012-06-21

申请号：US12971676

申请日：2010-12-17

申请人： Nayan Vinodbhai Patel ,  Michael Anthony Benjamin ,  Duane Douglas Thomsen ,  Alfred Albert Mancini

发明人： Nayan Vinodbhai Patel ,  Michael Anthony Benjamin ,  Duane Douglas Thomsen ,  Alfred Albert Mancini

IPC分类号： F02C7/22

CPC分类号： F23R3/28 ,  F23R3/34 ,  F23R3/60

摘要： A gas turbine engine fuel nozzle assembly includes a pilot fuel injector tip substantially centered about a centerline axis in an annular pilot inlet to a pilot mixer. A cross over arm extends across inlet to tip. Arm includes an arm fairing surrounding at least one fuel transfer tube to tip. A pilot nose cap is at an upstream end of tip. At least one of the cross over arm and the pilot nose cap includes a rounded forebody followed by a straight afterbody. Rounded forebody of pilot nose cap includes a substantially rounded dome extending forwardly from a rounded nose base and straight afterbody includes a substantially cylindrical nose afterbody parallel to a pilot nose centerline normal to nose base. An arm fairing surrounding fuel transfer tubes to tip includes rounded leading and trailing edges and a rectangular middle section therebetween having flat first and second sides.

摘要翻译： 燃气涡轮发动机燃料喷嘴组件包括引导燃料喷射器尖端，其基本上以中心线轴线为中心，位于环形先导进口到先导混合器中。 横跨臂跨越入口到尖端。 臂包括围绕至少一个燃料传输管的手臂整流装置。 先导鼻帽位于尖端的上游端。 交叉臂和先导鼻帽中的至少一个包括圆形的前身，后跟一个直的后身。 飞行员鼻盖的圆形前身包括从圆形鼻基部向前延伸的大致圆形的圆顶，并且直的后身体包括平行于与鼻底基准面的导向鼻中心线平行的基本上圆柱形的鼻后体。 围绕燃料转移管至顶部的臂整流罩包括圆形的前缘和后缘以及其间具有平坦的第一和第二侧的矩形中间部分。

公开(公告)号：US07878000B2

公开(公告)日：2011-02-01

申请号：US11312728

申请日：2005-12-20

申请人： Alfred Albert Mancini ,  Hukam Chand Mongia

发明人： Alfred Albert Mancini ,  Hukam Chand Mongia

IPC分类号： F02C1/00 ,  F02G3/00

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。

公开(公告)号：US20100251719A1

公开(公告)日：2010-10-07

申请号：US11648507

申请日：2006-12-29

申请人： Alfred Albert Mancini ,  Hukam Chand Mongia

发明人： Alfred Albert Mancini ,  Hukam Chand Mongia

IPC分类号： F02C7/22 ,  F02C7/12

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 centerbody positioned between the pilot mixer and the 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 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 centerbody includes a fuel manifold therein for providing fuel to the fuel injection ports and an air manifold therein for providing air to an aft portion of the pilot mixer and/or the aft portion of the annular cavity 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混合器，主混合器和位于先导混合器和主混合器之间的中心体。 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到所述环形空腔中的燃料喷射口; 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 。 中心体在其中包括用于向燃料喷射口提供燃料的燃料歧管及其中的空气歧管，用于向主混合器中的先导混合器的后部提供空气和/或环形空腔的后部。

公开(公告)号：US20070271927A1

公开(公告)日：2007-11-29

申请号：US11439321

申请日：2006-05-23

申请人： William Joseph Myers ,  Alfred Albert Mancini ,  George Chia-Chun Hsiao

发明人： William Joseph Myers ,  Alfred Albert Mancini ,  George Chia-Chun Hsiao

IPC分类号： F02C7/26

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

摘要： An apparatus 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装置，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。