专利快速检索-快速检索全球专利，免费商用专利数据库-IPRDB

1. 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.

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

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。

4. 发明申请

US20070028595A1 High pressure gas turbine engine having reduced emissions 审中-公开
标题翻译：具有减少排放的高压燃气涡轮发动机
公开(公告)号：US20070028595A1
公开(公告)日：2007-02-08
申请号：US11188483
申请日：2005-07-25
申请人： Hukam Mongia , George Hsiao , Shui-Chi Li , Shih-Yang Hsieh , Alfred Mancini , David Burrus , Marie McMasters , Duane Thomsen
发明人： Hukam Mongia , George Hsiao , Shui-Chi Li , Shih-Yang Hsieh , Alfred Mancini , David Burrus , Marie McMasters , Duane Thomsen
IPC分类号： F02K3/04 , F23R3/14
CPC分类号： F02K3/04 , F05D2270/082 , F23R3/06 , F23R3/14 , F23R3/286 , F23R3/343 , Y02T50/675 , Y02T50/677
摘要： A gas turbine engine having a longitudinal centerline axis therethrough, including a fan section at a forward end of the gas turbine engine for producing a first compressed air flow; a first compressor positioned downstream of the fan section and in flow communication with at least a portion of the first compressed air flow, wherein the first compressor produces a second compressed air flow having a designated pressure; a combustor positioned downstream of the first compressor and in flow communication with second compressed air flow, wherein the combustor produces combustion products from a mixture of fuel and air; a first turbine positioned downstream of the combustor and in flow communication with combustion products, wherein the first turbine powers the first compressor by means of a first rotatable drive shaft connected therebetween; and, a second turbine positioned downstream of the first turbine and in flow communication with the combustion products exiting the first turbine, wherein the second turbine powers the fan section by means of a second drive shaft connected therebetween. The gas turbine engine produces no more than a predetermined amount of emissions during an operating cycle.
摘要翻译：一种燃气涡轮发动机，其具有穿过其的纵向中心线轴线，包括在所述燃气涡轮发动机的前端处的风扇部分，用于产生第一压缩空气流; 第一压缩机，其位于所述风扇部分的下游并且与所述第一压缩空气流的至少一部分流动连通，其中所述第一压缩机产生具有指定压力的第二压缩空气流; 位于所述第一压缩机下游并与所述第二压缩空气流流动连通的燃烧器，其中所述燃烧器从燃料和空气的混合物产生燃烧产物; 位于燃烧器下游并与燃烧产物流动的第一涡轮机，其中第一涡轮机通过连接在其间的第一可旋转驱动轴来驱动第一压缩机; 以及位于第一涡轮机下游并与离开第一涡轮机的燃烧产物流动连通的第二涡轮机，其中第二涡轮机通过连接在其间的第二驱动轴为风扇部分供电。燃气涡轮发动机在操作循环期间产生不超过预定量的排放。

5. 发明申请

US20070157618A1 Methods and apparatus for assembling gas turbine engines 有权
标题翻译：燃气轮机发动机组装方法及装置
公开(公告)号：US20070157618A1
公开(公告)日：2007-07-12
申请号：US11329783
申请日：2006-01-11
申请人： John Manteiga , Duane Thomsen , Daniel Brown , John Brauer
发明人： John Manteiga , Duane Thomsen , Daniel Brown , John Brauer
IPC分类号： F23R3/00
CPC分类号： F23R3/60 , F02C3/14 , F23R3/50
摘要： A method for assembling a gas turbine engine is provided. The method includes providing a combustor liner support including a first portion formed with a plurality of circumferentially-spaced recessed areas, and a second portion extending from the first portion. The method also includes coupling the combustor liner support within a combustor such that during engine operations cooling air is channeled through the plurality of recessed areas to facilitate cooling the combustor liner support.
摘要翻译：提供一种用于组装燃气涡轮发动机的方法。该方法包括提供包括形成有多个周向间隔开的凹陷区域的第一部分和从第一部分延伸的第二部分的燃烧器衬套支撑件。该方法还包括将燃烧器衬套支撑件联接在燃烧器内，使得在发动机操作期间，冷却空气被引导通过多个凹陷区域以便于冷却燃烧器衬套支撑件。

你已经成功收藏专利！

检索式保存成功!

IPRDB

热门服务

关于我们

友情链接

联系方式