公开(公告)号：US07360364B2

公开(公告)日：2008-04-22

申请号：US11015175

申请日：2004-12-17

申请人： Allen Michael Danis ,  James Neil Cooper ,  Jeffrey Michael Martini

发明人： Allen Michael Danis ,  James Neil Cooper ,  Jeffrey Michael Martini

IPC分类号： F02C1/00 ,  F02G3/00

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。

公开(公告)号：US07121095B2

公开(公告)日：2006-10-17

申请号：US10638907

申请日：2003-08-11

申请人： Marie Ann McMasters ,  John Lawrence Vandike ,  James Neil Cooper ,  Michael Louis Vermeersch ,  Duane Douglas Thomsen ,  Allen Michael Danis

发明人： Marie Ann McMasters ,  John Lawrence Vandike ,  James Neil Cooper ,  Michael Louis Vermeersch ,  Duane Douglas Thomsen ,  Allen Michael Danis

IPC分类号： F02C1/00

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。

公开(公告)号：US08387358B2

公开(公告)日：2013-03-05

申请号：US12696241

申请日：2010-01-29

申请人： Allen Michael Danis ,  Steven Marakovits ,  Edward Joseph Stiftar

发明人： Allen Michael Danis ,  Steven Marakovits ,  Edward Joseph Stiftar

IPC分类号： F02C7/00

CPC分类号： F02C3/305 ,  F05D2240/35 ,  F05D2250/312 ,  F05D2250/711 ,  F05D2250/72 ,  F05D2270/082 ,  F23L7/005 ,  F23R3/16 ,  F23R3/50

摘要： A gas turbine engine steam injector includes an annular steam injection manifold aftwardly bounded by an aft manifold wall having steam injection holes disposed therethrough and located axially aft and radially inwardly of a diffuser outlet. An outer baffle wall around manifold has a curved convex surface which may generally conform to a streamline emanating from outlet. Holes may be circumferentially evenly distributed and non-uniformly sized around the aft manifold wall. Hollow struts extend between radially outer and inner bands of a diffuser and a steam supply header in steam supply communication with a fluid passage of at least one of the struts having a passage outlet open to steam cavity within cavity casing located inwardly of inner band. Openings are disposed in an aft cavity wall between cavity and the injector. Passages may be in only a non-uniformly distributed portion of the struts adjacent to each other.

摘要翻译： 燃气涡轮发动机蒸汽喷射器包括由后排管壁构成的环形蒸气喷射歧管，所述后部歧管壁具有穿过其设置的蒸汽喷射孔并且位于扩散器出口的轴向后部和径向向内。 歧管周围的外部挡板壁具有弯曲的凸形表面，该凸形表面通常可符合从出口发出的流线。 孔可以沿周向均匀分布，并且在尾部歧管壁周围不均匀。 空心支柱在扩散器的径向外部和内部带之间延伸，并且与至少一个支柱的流体通道的蒸汽供应连通的蒸汽供应头部具有在位于内部带内侧的腔体壳体内的通向蒸气腔的通道出口。 开口设置在腔和注射器之间的后空腔壁中。 通道可以仅在彼此相邻的支柱的非均匀分布的部分中。

公开(公告)号：US07036316B2

公开(公告)日：2006-05-02

申请号：US10687683

申请日：2003-10-17

申请人： Stephen John Howell ,  Allen Michael Danis

发明人： Stephen John Howell ,  Allen Michael Danis

IPC分类号： F23R3/04

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。 所述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

公开(公告)号：US07520134B2

公开(公告)日：2009-04-21

申请号：US11537066

申请日：2006-09-29

申请人： Mark D. Durbin ,  Allen Michael Danis ,  Timothy James Held ,  Daniel Durstock ,  James N. Cooper ,  Douglas Marti Fortuna

发明人： Mark D. Durbin ,  Allen Michael Danis ,  Timothy James Held ,  Daniel Durstock ,  James N. Cooper ,  Douglas Marti Fortuna

IPC分类号： F02C1/00

CPC分类号： F02C3/30 ,  F23D11/383 ,  F23D14/48 ,  F23L7/005 ,  F23R3/343

摘要： A method of operating a gas turbine engine is provided. The method includes discharging pilot fuel into a combustion chamber from a nozzle through at least one pilot fuel outlet defined in a tip of the nozzle, discharging steam from the nozzle through a plurality of steam outlets that are spaced circumferentially about the plurality of pilot fuel outlets, and discharging primary fuel from the nozzle through a plurality of primary fuel outlets that are circumferentially aligned with the plurality of steam outlets. To facilitate mixing the primary fuel with the steam, the primary fuel is discharged from the nozzle tip at an oblique angle with respect to a centerline extending through the nozzle tip.

摘要翻译： 提供了一种操作燃气涡轮发动机的方法。 该方法包括通过限定在喷嘴尖端中的至少一个引导燃料出口从喷嘴将导向燃料排放到燃烧室中，通过多个蒸汽出口排出蒸汽，多个蒸汽出口围绕多个引燃燃料出口周向间隔开 并且通过与所述多个蒸汽出口周向对齐的多个主燃料出口从所述喷嘴排出初级燃料。 为了便于将初级燃料与蒸汽混合，主燃料相对于延伸穿过喷嘴头的中心线以倾斜角度从喷嘴尖端排出。

公开(公告)号：US20080078180A1

公开(公告)日：2008-04-03

申请号：US11537066

申请日：2006-09-29

申请人： Mark D. Durbin ,  Allen Michael Danis ,  Timothy James Held ,  Daniel Durstock ,  James N. Cooper ,  Douglas Marti Fortuna

发明人： Mark D. Durbin ,  Allen Michael Danis ,  Timothy James Held ,  Daniel Durstock ,  James N. Cooper ,  Douglas Marti Fortuna

IPC分类号： F02C7/26

CPC分类号： F02C3/30 ,  F23D11/383 ,  F23D14/48 ,  F23L7/005 ,  F23R3/343

摘要： A method of operating a gas turbine engine is provided. The method includes discharging pilot fuel into a combustion chamber from a nozzle through at least one pilot fuel outlet defined in a tip of the nozzle, discharging steam from the nozzle through a plurality of steam outlets that are spaced circumferentially about the plurality of pilot fuel outlets, and discharging primary fuel from the nozzle through a plurality of primary fuel outlets that are circumferentially aligned with the plurality of steam outlets. To facilitate mixing the primary fuel with the steam, the primary fuel is discharged from the nozzle tip at an oblique angle with respect to a centerline extending through the nozzle tip.

摘要翻译： 提供了一种操作燃气涡轮发动机的方法。 该方法包括通过限定在喷嘴尖端中的至少一个引导燃料出口从喷嘴将导向燃料排放到燃烧室中，通过多个蒸汽出口排出蒸汽，多个蒸汽出口围绕多个引燃燃料出口周向间隔开 并且通过与所述多个蒸汽出口周向对齐的多个主燃料出口从所述喷嘴排出初级燃料。 为了便于将初级燃料与蒸汽混合，主燃料相对于延伸穿过喷嘴头的中心线以倾斜角度从喷嘴尖端排出。

公开(公告)号：US06976363B2

公开(公告)日：2005-12-20

申请号：US10638506

申请日：2003-08-11

申请人： Marie Ann McMasters ,  James Neil Cooper ,  Michael Louis Vermeersch ,  Duane Douglas Thomsen ,  Allen Michael Danis ,  Gregory Allen Cimmarusti

发明人： Marie Ann McMasters ,  James Neil Cooper ,  Michael Louis Vermeersch ,  Duane Douglas Thomsen ,  Allen Michael Danis ,  Gregory Allen 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.

摘要翻译： 一种用于燃气涡轮发动机的燃烧器穹顶组件，其具有延伸穿过其的纵向中心线轴线，包括：环形穹顶板，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，其中限定 每个开口之间包括形成在其中的冷却槽; 并且，位于圆顶板的上游的自由浮动旋流器与圆顶板中的每个开口基本对准，旋流器包括前部和后部。 每个旋流器的后部构造成使得在燃气涡轮发动机的运行期间空气流向冷却槽。 特别地，旋流器后部部分包括与圆顶板的前表面相邻延伸的大致环形的凸缘，其中与圆顶板的径向部分相邻的凸缘的圆周的相对部分基本上是线性的。

公开(公告)号：US20110185699A1

公开(公告)日：2011-08-04

申请号：US12696241

申请日：2010-01-29

申请人： Allen Michael Danis ,  Steven Marakovits ,  Edward Joseph Stiftar

发明人： Allen Michael Danis ,  Steven Marakovits ,  Edward Joseph Stiftar

IPC分类号： F02C7/00

CPC分类号： F02C3/305 ,  F05D2240/35 ,  F05D2250/312 ,  F05D2250/711 ,  F05D2250/72 ,  F05D2270/082 ,  F23L7/005 ,  F23R3/16 ,  F23R3/50

摘要： A gas turbine engine steam injector includes an annular steam injection manifold aftwardly bounded by an aft manifold wall having steam injection holes disposed therethrough and located axially aft and radially inwardly of a diffuser outlet. An outer baffle wall around manifold has a curved convex surface which may generally conform to a streamline emanating from outlet. Holes may be circumferentially evenly distributed and non-uniformally sized around the aft manifold wall. Hollow struts extend between radially outer and inner bands of a diffuser and a steam supply header in steam supply communication with a fluid passage of at least one of the struts having a passage outlet open to steam cavity within cavity casing located inwardly of inner band. Openings are disposed in an aft cavity wall between cavity and the injector. Passages may be in only a non-uniformally distributed portion of the struts that may be adjacent to each other.

摘要翻译： 燃气涡轮发动机蒸汽喷射器包括由后排管壁构成的环形蒸气喷射歧管，所述后部歧管壁具有穿过其设置的蒸汽喷射孔并且位于扩散器出口的轴向向后和径向向内。 歧管周围的外部挡板壁具有弯曲的凸形表面，该凸形表面通常可符合从出口发出的流线。 孔可以在后部歧管壁周围沿周向均匀分布和不均匀的尺寸。 空心支柱在扩散器的径向外部和内部带之间延伸，并且与至少一个支柱的流体通道的蒸汽供应连通的蒸汽供应头部具有在位于内部带内侧的腔体壳体内的通向蒸气腔的通道出口。 开口设置在腔和注射器之间的后空腔壁中。 通道可以仅在可以彼此相邻的支柱的非均匀分布的部分中。

公开(公告)号：US08631656B2

公开(公告)日：2014-01-21

申请号：US12059256

申请日：2008-03-31

申请人： Allen Michael Danis ,  Mark Anthony Mueller ,  Timothy James Held ,  Steven Marakovits

发明人： Allen Michael Danis ,  Mark Anthony Mueller ,  Timothy James Held ,  Steven Marakovits

IPC分类号： F23R3/34 ,  F02C7/236

CPC分类号： F23R3/50 ,  F23R2900/00013 ,  F23R2900/00014

摘要： A gas turbine engine combustor includes an annulus with one or more circular rows of burners and a means for providing a number of equiangular spaced apart flame temperature nonuniformities around the annulus during engine operation. The number of the flame temperature nonuniformities being equal to a circumferential acoustic mode to be attenuated in the combustor (i.e three, five, or seven). Fuel lines and/or water lines in supply communication with the burners and metering orifices in a portion of the fuel lines and/or the water lines may be used to produce the flame temperature nonuniformities. The annulus of the burners may have an equal number of equiangular spaced apart first and second arcuate segments of the burners and a means for operating the burners in the first segments and operating the burners in the second segments at different first and second flame temperatures respectively.

摘要翻译： 燃气涡轮发动机燃烧器包括具有一个或多个圆形排燃烧器的环形空间，以及用于在发动机运行期间在环空周围提供多个等角间隔开的火焰温度不均匀性的装置。 火焰温度不均匀性的数量等于在燃烧器中被衰减的周向声学模式（即三个，五个或七个）。 可以使用与燃料管线和/或水管线的一部分中的燃烧器和计量孔供应连通的燃料管线和/或水管线来产生火焰温度不均匀性。 燃烧器的环带可以具有相等数量的燃烧器的等角度间隔开的第一和第二弧形段，以及用于在第一段中操作燃烧器并分别在不同的第一和第二火焰温度下操作第二段中的燃烧器的装置。

公开(公告)号：US20090241548A1

公开(公告)日：2009-10-01

申请号：US12059256

申请日：2008-03-31

申请人： Allen Michael Danis ,  Mark Anthony Mueller ,  Timothy James Held ,  Steven Marakovits

发明人： Allen Michael Danis ,  Mark Anthony Mueller ,  Timothy James Held ,  Steven Marakovits

IPC分类号： F02C1/00

CPC分类号： F23R3/50 ,  F23R2900/00013 ,  F23R2900/00014

摘要： A gas turbine engine combustor includes an annulus with one or more circular rows of burners and a means for providing a number of equiangular spaced apart flame temperature nonuniformities around the annulus during engine operation. The number of the flame temperature nonuniformities being equal to a circumferential acoustic mode to be attenuated in the combustor (i.e three, five, or seven). Fuel lines and/or water lines in supply communication with the burners and metering orifices in a portion of the fuel lines and/or the water lines may be used to produce the flame temperature nonuniformities. The annulus of the burners may have an equal number of equiangular spaced apart first and second arcuate segments of the burners and a means for operating the burners in the first segments and operating the burners in the second segments at different first and second flame temperatures respectively.

摘要翻译： 燃气涡轮发动机燃烧器包括具有一个或多个圆形排燃烧器的环形空间，以及用于在发动机运行期间在环空周围提供多个等角间隔开的火焰温度不均匀性的装置。 火焰温度不均匀性的数量等于在燃烧器中被衰减的周向声学模式（即三个，五个或七个）。 可以使用与燃料管线和/或水管线的一部分中的燃烧器和计量孔供应连通的燃料管线和/或水管线来产生火焰温度不均匀性。 燃烧器的环带可以具有相等数量的燃烧器的等角度间隔开的第一和第二弧形段，以及用于在第一段中操作燃烧器并分别在不同的第一和第二火焰温度下操作第二段中的燃烧器的装置。