公开(公告)号：US06389815B1

公开(公告)日：2002-05-21

申请号：US09658872

申请日：2000-09-08

申请人： Harjit Singh Hura ,  Paul Edward Sabla ,  James Neil Cooper ,  Beverly Stephenson Duncan ,  Hukam Chand Mongia ,  Steven Joseph Lohmueller

发明人： Harjit Singh Hura ,  Paul Edward Sabla ,  James Neil Cooper ,  Beverly Stephenson Duncan ,  Hukam Chand Mongia ,  Steven Joseph Lohmueller

IPC分类号： F02C722

CPC分类号： F23R3/346 ,  F23C2201/20 ,  F23C2201/401

摘要： A two-stage fuel nozzle assembly for a gas turbine engine. The primary combustion region is centrally positioned and includes a fuel injector that is surrounded by one or more swirl chambers to provide a fuel air mixture that is ignited to define a first stage combustion zone. A secondary combustion region is provided by an annular housing that surrounds the primary combustion region, and it includes a secondary fuel injector having a radially outwardly directed opening and surrounded by an annular ring that includes openings for providing a swirl chamber for the secondary combustion region. Cooling air is directed angularly between the primary and secondary combustion zones to delay intermixing and thereby allow more complete combustion of the respective zones prior to their coalescing further downstream. The primary combustion region is activated during idle and low engine power conditions and both the primary and secondary combustion regions are activated during high engine power conditions.

摘要翻译： 一种用于燃气涡轮发动机的两级燃料喷嘴组件。 主燃烧区域居中定位并且包括燃料喷射器，燃料喷射器被一个或多个涡流室包围以提供点燃以限定第一级燃烧区的燃料空气混合物。 二次燃烧区域由围绕主燃烧区域的环形壳体提供，并且其包括具有径向向外指向的开口并由环形环围绕的二次燃料喷射器，该环形环包括用于为二次燃烧区域提供涡流室的开口。 冷却空气成角度地定向在主燃烧区域和次燃烧区域之间以延迟混合，从而允许相应区域在其进一步下游聚结之前更完全地燃烧。 初级燃烧区域在怠速和低发动机功率条件下被激活，并且主燃烧区域和次燃烧区域在高发动机功率条件期间被激活。

公开(公告)号：US06530227B1

公开(公告)日：2003-03-11

申请号：US09844411

申请日：2001-04-27

申请人： Craig Douglas Young ,  Paul Edward Sabla ,  Steven Clayton Vise

发明人： Craig Douglas Young ,  Paul Edward Sabla ,  Steven Clayton Vise

IPC分类号： F23R304

CPC分类号： F23D14/78 ,  F23R3/14 ,  F23R3/286

摘要： A one-piece deflector-flare cone assembly for a gas turbine engine combustor that facilitates extending a useful life of the combustor in a cost-effective and reliable manner is described. The one-piece assembly includes a deflector portion and a flare cone portion. The deflector portion includes an integral opening that extends through the deflector portion for receiving cooling fluid therein. The cooling opening extends circumferentially within the deflector portion. Cooling fluid discharged from the cooling opening is used for impingement cooling a portion of the flare cone portion to facilitate reducing an operating temperature and extending a useful life of the combustor.

摘要翻译： 描述了一种用于燃气涡轮发动机燃烧器的单件式偏转器 - 火炬锥形组件，其有助于以成本有效和可靠的方式延长燃烧器的使用寿命。 一体式组件包括偏转器部分和扩口锥部分。 偏转器部分包括延伸穿过偏转器部分的整体开口，用于在其中接收冷却流体。 冷却开口在偏转器部分内周向延伸。 从冷却开口排出的冷却流体用于冲击冷却火炬锥形部分的一部分，以便于降低工作温度并延长燃烧器的使用寿命。

公开(公告)号：US06546732B1

公开(公告)日：2003-04-15

申请号：US09844205

申请日：2001-04-27

申请人： Craig Douglas Young ,  Paul Edward Sabla ,  Steven Clayton Vise

发明人： Craig Douglas Young ,  Paul Edward Sabla ,  Steven Clayton Vise

IPC分类号： F23R306

CPC分类号： F23D14/78 ,  F23R3/14 ,  F23R3/286 ,  F23R2900/03042

摘要： A one-piece deflector-flare cone assembly for a gas turbine engine combustor that facilitates extending a useful life of the combustor in a cost-effective and reliable manner is described. The one-piece assembly includes a deflector portion and a flare cone portion. The deflector portion includes an integral opening that extends through the deflector portion for receiving cooling fluid therein. The cooling opening extends circumferentially within the deflector portion. Cooling fluid discharged from the cooling opening is used for film cooling a portion of the deflector portion to facilitate reducing an operating temperature and extending a useful life of the combustor.

摘要翻译： 描述了一种用于燃气涡轮发动机燃烧器的单件式偏转器 - 火炬锥形组件，其有助于以成本有效和可靠的方式延长燃烧器的使用寿命。 一体式组件包括偏转器部分和扩口锥部分。 偏转器部分包括延伸穿过偏转器部分的整体开口，用于在其中接收冷却流体。 冷却开口在偏转器部分内周向延伸。 从冷却开口排出的冷却流体用于薄膜冷却偏转器部分的一部分，以便于降低工作温度并延长燃烧器的使用寿命。