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1. 发明申请

US20060130485A1 Method and apparatus for assembling gas turbine engine combustors 有权
标题翻译：用于组装燃气涡轮发动机燃烧器的方法和装置
公开(公告)号：US20060130485A1
公开(公告)日：2006-06-22
申请号：US11015175
申请日：2004-12-17
申请人： Allen Danis , James Cooper , Jeffrey Martini
发明人： Allen Danis , James Cooper , Jeffrey Martini
IPC分类号： F23R3/42
CPC分类号： F23R3/60 , F23R3/08 , F23R2900/03044 , Y02T50/675
摘要： A method enables a combustor for a gas turbine engine to be assembled. The method includes coupling an inner liner to an outer liner such that a combustion chamber is defined therebetween, wherein the outer liner is fabricated from a plurality of panels coupled together, and coupling an outer support radially outward from the outer liner such that an outer passageway is defined between the outer liner and the outer support, wherein the outer support is configured to channel cooling air from the outer passageway towards at least a portion of the outer liner.
摘要翻译：一种方法使得能够组装用于燃气涡轮发动机的燃烧器。该方法包括将内衬套连接到外衬套，使得在其间限定燃烧室，其中外衬套由联接在一起的多个面板制成，并且将外支撑件从外衬里径向向外联接，使得外套管限定在外衬套和外支撑件之间，其中外支撑件构造成将冷却空气从外通道向至外部衬套的至少一部分引导。

2. 发明申请

US20050034459A1 Combustor dome assembly of a gas turbine engine having a contoured swirler 失效
公开(公告)号：US20050034459A1
公开(公告)日：2005-02-17
申请号：US10638506
申请日：2003-08-11
申请人： Marie McMasters , James Cooper , Michael Vermeersch , Duane Thomsen , Allen Danis , Gregory Cimmarusti
发明人： Marie McMasters , James Cooper , Michael Vermeersch , Duane Thomsen , Allen Danis , Gregory Cimmarusti
IPC分类号： F23R3/14 , F23R3/00 , F23R3/08 , F23R3/10 , F23R3/50 , F23R3/42
CPC分类号： F23R3/002 , F23R3/10 , F23R3/50
摘要： A combustor dome assembly for a gas turbine engine having a longitudinal centerline axis extending therethrough includes: an annular dome plate having an inner portion, an outer portion, a forward surface, and a plurality of circumferentially spaced openings formed therein, wherein a radial section defined between each of the openings includes a cooling trough formed therein; and, a free floating swirler located upstream of the dome plate in substantial alignment with each of the openings in the dome plate, the swirler including a forward portion and an aft portion. The aft portion of each swirler is configured so as to permit air flow to the cooling trough during operation of the gas turbine engine. In particular, the swirler aft portion includes a substantially annular flange extending adjacent to the forward surface of the dome plate, wherein opposing portions of a circumference for the flange adjacent the radial sections of the dome plate are substantially linear.

3. 发明申请

US20070101726A1 Methods and apparatus for injecting fluids into a turbine engine 有权
标题翻译：将流体注入涡轮发动机的方法和装置
公开(公告)号：US20070101726A1
公开(公告)日：2007-05-10
申请号：US11268183
申请日：2005-11-07
申请人： Mark Durbin , Allen Danis , Timothy Held , James Cooper , Douglas Fortuna , Daniel Durstock
发明人： Mark Durbin , Allen Danis , Timothy Held , James Cooper , Douglas Fortuna , Daniel Durstock
IPC分类号： F02C3/30
CPC分类号： F02C3/30 , F05D2250/31 , F05D2250/314 , F23D14/58 , F23D2900/00014 , F23L7/005 , F23R3/343
摘要： A method facilitates operating a gas turbine engine. The method comprises supplying steam to a nozzle, supplying primary fuel to the nozzle, discharging the steam into a combustor from a plurality of circumferentially-spaced steam outlets defined in a tip of the nozzle, and discharging the primary fuel into the combustor from at least one outlet that is spaced circumferentially between the steam outlets.
摘要翻译：一种方法便于操作燃气涡轮发动机。该方法包括向喷嘴供应蒸汽，向喷嘴供应初级燃料，将蒸汽从限定在喷嘴的尖端中的多个周向隔开的蒸汽出口排出到燃烧器中，并将主燃料从至少排出到燃烧器中一个在蒸汽出口之间周向隔开的出口。

4. 发明申请

US20050103020A1 Method and apparatus to decrease combustor emissions 有权
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.

5. 发明申请

US20050034461A1 Combustor dome assembly of a gas turbine engine having improved deflector plates 有权
标题翻译：具有改进的偏转板的燃气涡轮发动机的燃烧器顶盖组件
公开(公告)号：US20050034461A1
公开(公告)日：2005-02-17
申请号：US10638907
申请日：2003-08-11
申请人： Marie McMasters , John Vandike , James Cooper , Michael Vermeersch , Duane Thomsen , Allen Danis
发明人： Marie McMasters , John Vandike , James Cooper , Michael Vermeersch , Duane Thomsen , Allen Danis
IPC分类号： F23R3/10 , F23R3/14 , F23R3/42 , F23R3/60
CPC分类号： F23R3/10 , F23R2900/00005
摘要： A combustor dome assembly for a gas turbine engine having a longitudinal centerline axis extending therethrough, including: an annular dome plate having an inner portion, an outer portion, a forward surface, and a plurality of circumferentially spaced openings formed therein, wherein a radial section defined between each of the openings includes a cooling trough formed therein; an outer cowl connected to the dome plate outer portion at a downstream end thereof; an inner cowl connected to the dome plate inner portion at a downstream end thereof; and, a deflector plate connected to and positioned aft of each opening in the dome plate. Each deflector plate further includes: an annular section at an upstream end thereof having a forward end, an aft end, an inner surface and an outer surface; a substantially planar flange connected to the aft end of the annular section, the planar flange including an outer circumferential surface, an inner circumferential surface, a first radial surface, a second radial surface, and an opening therein sized to the inner surface of the annular section so as to form opposing radial sections; a first flange connected to the outer circumferential surface of the planar flange at a predetermined angle thereto; and, a second flange connected to the inner circumferential surface of the planar flange at a predetermined angle thereto. The first and second radial sections of the deflector plate planar flange are configured so at least a portion of the dome plate cooling trough is in flow communication with a combustion chamber downstream of said dome plate.
摘要翻译：一种用于燃气涡轮发动机的燃烧器圆顶组件，其具有延伸穿过其的纵向中心线轴线，包括：环形圆顶板，其具有形成在其中的内部部分，外部部分，前表面和多个周向间隔开的开口，每个开口之间限定的冷却槽包括：在其下游端与圆顶板外部连接的外罩; 在其下游端连接到圆顶板内部的内罩; 以及连接到顶板中的每个开口的后部并定位的偏转板。每个偏转板还包括：在其上游端的环形部分，其具有前端，后端，内表面和外表面; 连接到所述环形部分的后端的基本上平面的凸缘，所述平面凸缘包括外周面，内周面，第一径向表面，第二径向表面和开口，其尺寸设置成所述环形部分的内表面以形成相对的径向部分; 与所述平面凸缘的外周面以预定角度连接的第一凸缘; 以及与所述平面凸缘的内周面以规定角度连接的第二凸缘。偏转板平面凸缘的第一和第二径向部分构造成使得圆顶板冷却槽的至少一部分与所述圆顶板的下游的燃烧室流动连通。

6. 发明申请

US20060130486A1 Method and apparatus for assembling gas turbine engine combustors 审中-公开
标题翻译：用于组装燃气涡轮发动机燃烧器的方法和装置
公开(公告)号：US20060130486A1
公开(公告)日：2006-06-22
申请号：US11017186
申请日：2004-12-17
申请人： Allen Danis , Timothy Held
发明人： Allen Danis , Timothy Held
IPC分类号： F23R3/42
CPC分类号： F23R3/06 , F23R3/002 , F23R2900/00014 , Y02T50/675
摘要： A method enables the operation of a gas turbine engine. The method comprises channeling airflow into a cooling passageway defined between the combustor casing and an inner liner of the combustor, wherein the inner liner is fabricated from a plurality of panels coupled together, channeling airflow into a cooling passageway defined between the combustor casing and an outer liner of the combustor; wherein the outer liner is fabricated from a plurality of panels coupled together, and channeling dilution airflow into a combustion chamber defined between the inner and outer liners, through a plurality of openings formed within at least one panel within at least one of the inner liner panels and the outer liner panels, wherein the plurality of openings are non-circular.
摘要翻译：一种方法使得能够操作燃气涡轮发动机。该方法包括将气流引导到限定在燃烧器壳体和燃烧器的内衬之间的冷却通道中，其中内衬由多个联接在一起的面板制成，将气流引导到限定在燃烧器壳体和外壳之间的冷却通道燃烧室内衬; 其中所述外衬套由耦合在一起的多个面板制成，并且通过形成在所述内衬板内的至少一个内的至少一个面板内的多个开口将稀释气流引导到限定在所述内衬层和所述内衬之间的燃烧室中和外衬板，其中多个开口是非圆形的。

7. 发明申请

US20050081526A1 Methods and apparatus for cooling turbine engine combustor exit temperatures 失效
标题翻译：用于冷却涡轮发动机燃烧器出口温度的方法和装置
公开(公告)号：US20050081526A1
公开(公告)日：2005-04-21
申请号：US10687683
申请日：2003-10-17
申请人： Stephen Howell , Allen Danis
发明人： Stephen Howell , Allen Danis
IPC分类号： F02C7/18 , F23R3/00 , F23R3/06 , F23R3/42
CPC分类号： F23R3/06 , F23R3/002 , F23R2900/03044
摘要： A method facilitates assembling a combustor for a gas turbine engine. The method comprises coupling an inner liner to an outer liner such that a combustion chamber is defined therebetween, positioning an outer support a distance radially outward from the outer liner, and positioning an inner support a distance radially inward from the inner liner. The method also comprises forming at least two rows of impingement openings extending through at least one of the inner support and the outer support for channeling impingement cooling air therethrough towards at least one of the inner liner and the outer liner, and forming at least one row of dilution openings extending through at least one of the inner liner and the outer liner for channeling dilution cooling air therethrough into the combustion chamber
摘要翻译：一种方法有利于组装用于燃气涡轮发动机的燃烧器。该方法包括将内衬套连接到外衬套，使得在其间限定燃烧室，将外支撑件从外衬里径向向外定位，并将内支撑件从内衬径向向内定位。该方法还包括形成延伸穿过内部支撑件和外部支撑件中的至少一个的至少两排冲击开口，用于将冲击冷却空气穿过其中穿过至少一个内衬套和外衬套，并形成至少一排的稀释开口延伸穿过内衬和外衬里中的至少一个，用于将稀释的冷却空气引导进入燃烧室

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