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1. 发明授权

US06381964B1 Multiple annular combustion chamber swirler having atomizing pilot 有权
标题翻译：具有雾化飞行员的多环形燃烧室旋流器
公开(公告)号：US06381964B1
公开(公告)日：2002-05-07
申请号：US09675664
申请日：2000-09-29
申请人： Byron Andrew Pritchard, Jr. , Allen Michael Danis , Michael Jerome Foust , Mark David Durbin , Hukam Chand Mongia
发明人： Byron Andrew Pritchard, Jr. , Allen Michael Danis , Michael Jerome Foust , Mark David Durbin , Hukam Chand Mongia
IPC分类号： F02G300
CPC分类号： F23R3/14 , F23R3/286 , F23R3/343
摘要： A mixer assembly for use in a combustion chamber of a gas turbine engine. The assembly includes a pilot mixer and a main mixer. The pilot mixer includes an annular pilot housing having a hollow interior, a pilot fuel nozzle mounted in the housing adapted for dispensing droplets of fuel to the hollow interior of the pilot housing, and a plurality of concentrically mounted axial swirlers positioned upstream from the pilot fuel nozzle. Each of the swirlers has a plurality of vanes for swirling air traveling through the respective swirler to mix air and the droplets of fuel dispensed by the pilot fuel nozzle. The main mixer includes a main housing surrounding the pilot housing defining an annular cavity, a plurality of fuel injection ports for introducing fuel into the cavity, and a swirler positioned upstream from the plurality of fuel injection ports having a plurality of vanes for swirling air traveling through the swirler to mix air and the droplets of fuel dispensed by the fuel injection ports.
摘要翻译：一种用于燃气涡轮发动机的燃烧室的混合器组件。该组件包括一个先导式混合器和一个主混合器。先导式混合器包括具有中空内部的环形导向壳体，安装在壳体中的引燃燃料喷嘴，其适于将燃料液滴分配到先导壳体的中空内部;以及多个同心安装的轴向旋流器，其位于导向燃料喷嘴。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引燃燃料喷嘴分配的燃料的液滴。主混合器包括围绕引导壳体的主壳体，其限定环形空腔，用于将燃料引入空腔中的多个燃料喷射端口和位于多个燃料喷射端口的上游的旋流器，其具有用于旋转空气行进的多个叶片通过旋流器来混合空气和由燃料喷射口分配的燃料的液滴。

2. 发明授权

US06609377B2 Multiple injector combustor 失效
公开(公告)号：US06609377B2
公开(公告)日：2003-08-26
申请号：US10210298
申请日：2002-07-31
申请人： Mark David Durbin , Hukam Chand Mongia
发明人： Mark David Durbin , Hukam Chand Mongia
IPC分类号： F02C100
CPC分类号： F23R3/14 , F23R3/28 , Y02T50/675
摘要： A mixer for use in a combustion chamber of a gas turbine engine. The mixer includes an annular housing having an upstream end, a downstream end, a mount for attaching the housing to an upstream end of the combustion chamber, and an interior surface defining a hollow interior. The mixer also has a first swirler mounted inside the annular housing including a plurality of vanes extending inward from the housing for swirling air traveling through the housing. In addition, the mixer includes an annular fuel injector having a plurality of fuel injection ports arranged in a generally circular pattern mounted inside the first swirler for releasing droplets of fuel into swirling air downstream from the fuel injector. Further, the mixer has a second swirler mounted inside the fuel injector including a plurality of vanes extending inward from the injector for swirling air traveling through the housing downstream from the fuel injector.

3. 发明授权

US06474071B1 Multiple injector combustor 失效
标题翻译：多喷射器燃烧器
公开(公告)号：US06474071B1
公开(公告)日：2002-11-05
申请号：US09675668
申请日：2000-09-29
申请人： Mark David Durbin , Hukam Chand Mongia
发明人： Mark David Durbin , Hukam Chand Mongia
IPC分类号： F02C100
CPC分类号： F23R3/14 , F23R3/28 , Y02T50/675
摘要： A mixer for use in a combustion chamber of a gas turbine engine. The mixer includes an annular housing having an upstream end, a downstream end, a mount for attaching the housing to an upstream end of the combustion chamber, and an interior surface defining a hollow interior. The mixer also has a first swirler mounted inside the annular housing including a plurality of vanes extending inward from the housing for swirling air traveling through the housing. In addition, the mixer includes an annular fuel injector having a plurality of fuel injection ports arranged in a generally circular pattern mounted inside the first swirler for releasing droplets of fuel into swirling air downstream from the fuel injector. Further, the mixer has a second swirler mounted inside the fuel injector including a plurality of vanes extending inward from the injector for swirling air traveling through the housing downstream from the fuel injector.
摘要翻译：一种用于燃气涡轮发动机的燃烧室的混合器。混合器包括具有上游端，下游端，用于将壳体附接到燃烧室的上游端的安装件以及限定中空内部的内表面的环形壳体。混合器还具有安装在环形壳体内部的第一旋流器，其包括从壳体向内延伸的多个叶片，用于旋转通过壳体的空气。此外，混合器包括环形燃料喷射器，其具有以安装在第一旋流器内部的大致圆形图案布置的多个燃料喷射口，用于将燃料液滴释放到燃料喷射器下游的旋转空气中。此外，混合器具有安装在燃料喷射器内部的第二旋流器，其包括从喷射器向内延伸的多个叶片，用于在燃料喷射器的下游行进通过壳体的旋转空气。

4. 发明授权

US06363726B1 Mixer having multiple swirlers 有权
标题翻译：搅拌机有多个旋流器
公开(公告)号：US06363726B1
公开(公告)日：2002-04-02
申请号：US09675666
申请日：2000-09-29
申请人： Mark David Durbin , Timothy James Held , Hukam Chand Mongia
发明人： Mark David Durbin , Timothy James Held , Hukam Chand Mongia
IPC分类号： F23R360
CPC分类号： F23R3/343 , F23D2900/00015 , F23R3/14 , F23R3/286
摘要： A mixer assembly for use in a combustion chamber of a gas turbine engine. The assembly includes a pilot mixer and a main mixer. The pilot mixer includes an annular pilot housing having a hollow interior, a pilot fuel nozzle mounted in the housing and adapted for dispensing droplets of fuel to the hollow interior of the pilot housing, and one or more axial swirlers positioned upstream from the pilot fuel nozzle. The main mixer includes a main housing surrounding the pilot housing and defining an annular cavity, an annular fuel injector having a plurality of fuel injection ports arranged in a circular pattern surrounding the pilot housing and mounted inside the annular cavity of the main mixer for releasing droplets of fuel into swirling air downstream from the fuel injector, and one or more axial swirlers positioned upstream from the plurality of fuel injection ports.
摘要翻译：一种用于燃气涡轮发动机的燃烧室的混合器组件。该组件包括一个先导式混合器和一个主混合器。先导式混合器包括具有中空内部的环形导向壳体，安装在壳体中的适于将燃料液滴分配到导向壳体的中空内部的引燃燃料喷嘴以及位于导向燃料喷嘴上游的一个或多个轴向旋流器。主混合器包括围绕引导壳体并限定环形空腔的主壳体，环形燃料喷射器，其具有围绕引燃壳体布置成圆形图案的多个燃料喷射端口，并且安装在主混合器的环形空腔内部以释放液滴的燃料喷射到燃料喷射器下游的旋转空气中，以及位于多个燃料喷射口的上游的一个或多个轴向旋流器。

5. 发明授权

US06415594B1 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：US06415594B1
公开(公告)日：2002-07-09
申请号：US09583412
申请日：2000-05-31
申请人： Mark David Durbin , Timothy James Held
发明人： Mark David Durbin , Timothy James Held
IPC分类号： F02G300
CPC分类号： F23R3/286 , F23R3/34 , F23R3/50
摘要： A gas turbine engine includes a combustor system to reduce an amount of nitrogen oxide emissions formed by the gas turbine engine. The combustor system includes a combustor including a first annular dome. A centerbody is secured within the dome and includes at least one orifice for supplying fuel to the dome. An inner swirler is attached to the centerbody and an outer swirler is attached radially outward from the inner swirler such that a leading edge of the inner swirler and a leading edge of the centerbody are disposed upstream from a leading edge of the outer swirler.
摘要翻译：燃气涡轮发动机包括用于减少由燃气涡轮发动机形成的氮氧化物排放量的燃烧器系统。燃烧器系统包括包括第一环形圆顶的燃烧器。中心体被固定在圆顶内，并且包括至少一个用于向穹顶供应燃料的孔口。内旋流器附接到中心体，并且外旋流器从内旋流器径向向外附接，使得内旋流器的前缘和中心体的前缘设置在外旋流器的前缘的上游。

6. 发明授权

US09719685B2 System and method for flame stabilization 有权
公开(公告)号：US09719685B2
公开(公告)日：2017-08-01
申请号：US13557750
申请日：2012-07-25
申请人： Mark David Durbin , Mark Anthony Mueller , Lance Kenneth Blakeman , David Albin Lind
发明人： Mark David Durbin , Mark Anthony Mueller , Lance Kenneth Blakeman , David Albin Lind
IPC分类号： F23R3/28 , F23R3/34
CPC分类号： F23R3/286 , F23D2900/00008 , F23D2900/00015 , F23R3/346
摘要： A system and method for flame stabilization is provided that forestalls incipient lean blow out by improving flame stabilization. A combustor profile is selected that maintains desired levels of power output while minimizing or eliminating overboard air bleed and minimizing emissions. The selected combustor profile maintains average shaft power in a range of from approximately 50% up to full power while eliminating overboard air bleed in maintaining such power settings. Embodiments allow for a combustor to operate with acceptable emissions at lower flame temperature. Because the combustor can operate at lower bulk flame temperatures during part power operation, the usage of inefficient overboard bleed can be reduced or even eliminated.

7. 发明申请

US20130152597A1 SYSTEM AND METHOD FOR FLAME STABILIZATION 有权
标题翻译：用于火焰稳定的系统和方法
公开(公告)号：US20130152597A1
公开(公告)日：2013-06-20
申请号：US13557750
申请日：2012-07-25
申请人： Mark David Durbin , Mark Anthony Mueller , Lance Kenneth Blakeman , David Albin Lind
发明人： Mark David Durbin , Mark Anthony Mueller , Lance Kenneth Blakeman , David Albin Lind
IPC分类号： F02C9/00 , F02C6/08 , F02C9/26 , F02C7/228
CPC分类号： F23R3/286 , F23D2900/00008 , F23D2900/00015 , F23R3/346
摘要： A system and method for flame stabilization is provided that forestalls incipient lean blow out by improving flame stabilization. A combustor profile is selected that maintains desired levels of power output while minimizing or eliminating overboard air bleed and minimizing emissions. The selected combustor profile maintains average shaft power in a range of from approximately 50% up to full power while eliminating overboard air bleed in maintaining such power settings. Embodiments allow for a combustor to operate with acceptable emissions at lower flame temperature. Because the combustor can operate at lower bulk flame temperatures during part power operation, the usage of inefficient overboard bleed can be reduced or even eliminated.
摘要翻译：提供了一种用于火焰稳定化的系统和方法，其通过改善火焰稳定性来防止初始稀薄吹出。选择燃烧器型材，其保持期望的功率输出水平，同时最小化或消除舷外排气并最小化排放。所选择的燃烧器型材将平均轴功率保持在大约50％到全功率的范围内，同时在保持这种功率设置的同时消除舷外空气泄漏。实施例允许燃烧器在较低火焰温度下以可接受的排放物操作。因为在部分动力运行期间燃烧器可以在较低的主体火焰温度下操作，所以可以减少甚至消除无效率的舷外排放的使用。

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