EFFUSION COOLED DUAL WALL GAS TURBINE COMBUSTORS
    1.
    发明申请
    EFFUSION COOLED DUAL WALL GAS TURBINE COMBUSTORS 有权
    有效冷却双壁气体涡轮搅拌机

    公开(公告)号:US20110023495A1

    公开(公告)日:2011-02-03

    申请号:US12512816

    申请日:2009-07-30

    IPC分类号: F02C7/12

    摘要: A gas turbine engine combustor is provided. An inner liner has an upstream end and a downstream end and extends in an axial direction between the upstream and downstream ends. A dual wall outer liner has a hot wall, a cold wall at least partially surrounding the hot wall, an upstream end, and a downstream end. The outer liner extends in the axial direction between the upstream and downstream ends. A dome assembly is coupled between the upstream ends of the inner and outer liners to define a combustion chamber between the inner liner and the hot wall of the outer liner. Effusion cooling holes are disposed in the hot wall, including a first row disposed at a tangential angle of between about 70° and about 90° and a second row disposed at a tangential angle of between about 0° and about 20°.

    摘要翻译: 提供燃气涡轮发动机燃烧器。 内衬具有上游端和下游端,并且在上游端和下游端之间沿轴向方向延伸。 双壁外衬套具有热壁,至少部分围绕热壁的冷壁,上游端和下游端。 外衬套在上游和下游端之间沿轴向方向延伸。 圆顶组件联接在内衬和外衬垫的上游端之间,以在内衬层和外衬套的热壁之间限定燃烧室。 排出冷却孔设置在热壁中,包括设置在约70°至约90°之间的切线角度的第一排和以大约0°至大约20°之间的切线角设置的第二排。

    Annular rich-quench-lean gas turbine combustors with plunged holes
    4.
    发明授权
    Annular rich-quench-lean gas turbine combustors with plunged holes 有权
    环状富稀燃气涡轮燃烧器,带有漏洞

    公开(公告)号:US08171740B2

    公开(公告)日:2012-05-08

    申请号:US12394725

    申请日:2009-02-27

    IPC分类号: F23R3/06 F23R3/50

    CPC分类号: F23R3/045 F23R3/50 Y02T50/675

    摘要: A combustor may include an outer liner having a first group of air admission holes and defining a plurality of outer liner regions. The combustor may further include an inner liner having a second group of air admission holes and defining a plurality of inner liner regions. The first group of air admission holes within a respective outer liner region may include a first plunged air admission hole approximately axially aligned with the respective fuel injector, a second plunged air admission hole approximately on the outer boundary line between the respective outer liner region and a first adjacent outer liner region, the first air admission hole being downstream of the second air admission hole, and a third plunged air admission hole approximately on the outer boundary line between the respective outer liner region and a second adjacent outer liner region.

    摘要翻译: 燃烧器可以包括具有第一组进气孔并且限定多个外衬里区域的外衬套。 燃烧器还可以包括具有第二组进气孔并限定多个内衬区域的内衬。 在相应的外衬里区域内的第一组进气孔可以包括大致与相应的燃料喷射器轴向对准的第一入口进气孔,大致在相应的外衬里区域和相应的外衬里区域之间的外边界线上的第二穿入空气进入孔 第一相邻的外衬垫区域,第一进气孔位于第二进气孔的下游,第三入口孔大致在相应的外衬垫区域和第二相邻的外衬里区域之间的外边界线上。

    PLUNGED HOLE ARRANGEMENT FOR ANNULAR RICH-QUENCH-LEAN GAS TURBINE COMBUSTORS
    5.
    发明申请
    PLUNGED HOLE ARRANGEMENT FOR ANNULAR RICH-QUENCH-LEAN GAS TURBINE COMBUSTORS 有权
    环形精密气体涡轮搅拌机的孔盖布置

    公开(公告)号:US20100218503A1

    公开(公告)日:2010-09-02

    申请号:US12394656

    申请日:2009-02-27

    IPC分类号: F23R3/10 F02C7/22

    CPC分类号: F23R3/06 F23R3/50 Y02T50/675

    摘要: A combustor may include an outer liner having a first row and a second row of circumferentially distributed air admission holes. The second row of the outer liner may be downstream of the first row of the outer liner, and the air admission holes of the first row of the outer liner may be larger than the air admission holes of the second row of the outer liner. An inner liner is circumscribed by the outer liner and has a third and fourth row of circumferentially distributed air admission holes. The air admission holes of the third row of the inner liner may be larger than the air admission holes of the fourth row of the inner liner. The inner and outer liners may form a combustion chamber, and at least a portion of the air admission holes of the first, second, third, or fourth rows may be plunged.

    摘要翻译: 燃烧器可以包括具有第一排和第二排周向分布的进气孔的外衬套。 外衬套的第二排可以在外衬套的第一排的下游,并且外衬套的第一排的进气孔可以大于外衬套的第二排的进气孔。 内衬由外衬套限定,并具有第三排和第四排周向分布的进气孔。 内衬的第三排的进气孔可以大于内衬的第四排的进气孔。 内衬层和外衬层可以形成燃烧室,并且第一,第二,第三或第四排的进气孔的至少一部分可能被冲入。

    Plunged hole arrangement for annular rich-quench-lean gas turbine combustors
    6.
    发明授权
    Plunged hole arrangement for annular rich-quench-lean gas turbine combustors 有权
    环形富燃冷式燃气轮机的钻孔安排

    公开(公告)号:US08141365B2

    公开(公告)日:2012-03-27

    申请号:US12394656

    申请日:2009-02-27

    IPC分类号: F23R3/06 F23R3/50

    CPC分类号: F23R3/06 F23R3/50 Y02T50/675

    摘要: A combustor may include an outer liner having a first row and a second row of circumferentially distributed air admission holes. The second row of the outer liner may be downstream of the first row of the outer liner, and the air admission holes of the first row of the outer liner may be larger than the air admission holes of the second row of the outer liner. An inner liner is circumscribed by the outer liner and has a third and fourth row of circumferentially distributed air admission holes. The air admission holes of the third row of the inner liner may be larger than the air admission holes of the fourth row of the inner liner. The inner and outer liners may form a combustion chamber, and at least a portion of the air admission holes of the first, second, third, or fourth rows may be plunged.

    摘要翻译: 燃烧器可以包括具有第一排和第二排周向分布的进气孔的外衬套。 外衬套的第二排可以在外衬套的第一排的下游,并且外衬套的第一排的进气孔可以大于外衬套的第二排的进气孔。 内衬由外衬套限定,并具有第三排和第四排周向分布的进气孔。 内衬的第三排的进气孔可以大于内衬的第四排的进气孔。 内衬层和外衬层可以形成燃烧室,并且第一,第二,第三或第四排的进气孔的至少一部分可能被冲入。

    ANNULAR RICH-QUENCH-LEAN GAS TURBINE COMBUSTORS WITH PLUNGED HOLES
    7.
    发明申请
    ANNULAR RICH-QUENCH-LEAN GAS TURBINE COMBUSTORS WITH PLUNGED HOLES 有权
    具有多孔的环形精密气体涡轮机

    公开(公告)号:US20100218504A1

    公开(公告)日:2010-09-02

    申请号:US12394725

    申请日:2009-02-27

    IPC分类号: F23R3/50 F02C7/22

    CPC分类号: F23R3/045 F23R3/50 Y02T50/675

    摘要: A combustor may include an outer liner having a first group of air admission holes and defining a plurality of outer liner regions. The combustor may further include an inner liner having a second group of air admission holes and defining a plurality of inner liner regions. The first group of air admission holes within a respective outer liner region may include a first plunged air admission hole approximately axially aligned with the respective fuel injector, a second plunged air admission hole approximately on the outer boundary line between the respective outer liner region and a first adjacent outer liner region, the first air admission hole being downstream of the second air admission hole, and a third plunged air admission hole approximately on the outer boundary line between the respective outer liner region and a second adjacent outer liner region.

    摘要翻译: 燃烧器可以包括具有第一组进气孔并且限定多个外衬里区域的外衬套。 燃烧器还可以包括具有第二组进气孔并限定多个内衬区域的内衬。 在相应的外衬里区域内的第一组进气孔可以包括大致与相应的燃料喷射器轴向对准的第一入口进气孔,大致在相应的外衬里区域和相应的外衬里区域之间的外边界线上的第二穿入空气进入孔 第一相邻的外衬垫区域,第一进气孔位于第二进气孔的下游,第三入口孔大致在相应的外衬垫区域和第二相邻的外衬里区域之间的外边界线上。

    LOW EMISSION COMBUSTION SYSTEMS AND METHODS FOR GAS TURBINE ENGINES
    8.
    发明申请
    LOW EMISSION COMBUSTION SYSTEMS AND METHODS FOR GAS TURBINE ENGINES 审中-公开
    低排放燃烧系统和燃气涡轮发动机的方法

    公开(公告)号:US20110219779A1

    公开(公告)日:2011-09-15

    申请号:US12721774

    申请日:2010-03-11

    IPC分类号: F02C9/00 F02C7/22 F02C3/14

    摘要: A combustion system for a gas turbine engine is provided. The system includes a forward liner; an aft liner; a combustion chamber formed by the forward liner and the aft liner, the combustion chamber defining a lean combustion zone and a pilot combustion zone; a premixing zone coupled to the combustion chamber; a pilot fuel injector coupled to the combustion chamber and configured to deliver a first flow of fuel to the pilot combustion zone; and a slinger unit configured to deliver a second flow of fuel to the premixing zone such that the second flow of fuel is mixed with air in the premixing zone and directed into the lean combustion zone of the combustion chamber.

    摘要翻译: 提供了一种燃气轮机的燃烧系统。 该系统包括一个前向衬垫; 尾衬; 所述燃烧室由所述前部衬套和所述后部衬套形成,所述燃烧室限定稀燃燃烧区域和先导燃烧区域; 耦合到所述燃烧室的预混合区; 联接到所述燃烧室并被配置为将第一燃料流输送到所述先导燃烧区的引燃燃料喷射器; 以及抛油环单元,其构造成将第二燃料流输送到预混合区域,使得第二燃料流与预混合区域中的空气混合并引导到燃烧室的稀燃燃烧区域。