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公开(公告)号：EP2253887B1
公开(公告)日：2019-04-17
申请号：EP10163039.0
申请日：2010-05-17
发明人： Kim, Won-Wook , Snyder, Timothy S.
IPC分类号： F23R3/06
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公开(公告)号：EP2290289A3
公开(公告)日：2014-10-15
申请号：EP10251531.9
申请日：2010-08-31
发明人： Snyder, Timothy S. , Kim, Won-Wook
CPC分类号： F23R3/06 , F23R3/50 , Y02T50/675
摘要： A gas turbine engine has a combustor module including an annular combustor (26) having a liner assembly that defines an annular combustion chamber (30) and includes a circumferential row of a plurality of relatively large combustion dilution air admission holes (116) and a circumferential row of a plurality of smaller quench air admission holes (120) disposed downstream with respect to the flow of combustion gas products. The plurality of quench air admission holes (120) are arranged with respect to the plurality of relatively large dilution air admission holes (116) disposed upstream thereof such that there is associated with each dilution air admission hole (116) a first quench air admission hole (120) and a second quench air admission hole (120), the first quench air admission hole (120) being offset laterally in a first lateral direction and the second quench air admission hole (120) being offset laterally in a second lateral direction opposite to the first direction.
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公开(公告)号：EP2253887A3
公开(公告)日：2014-08-20
申请号：EP10163039.0
申请日：2010-05-17
发明人： Kim, Won-Wook , Snyder, Timothy S.
IPC分类号： F23R3/06
CPC分类号： F23R3/06
摘要： A combustor (20) for a gas turbine engine includes a forward bulkhead (22), an inner radial combustor wall (26) and an outer radial combustor wall (28). The forward bulkhead has a plurality of circumferentially disposed injector apertures (34). The inner radial combustor wall is attached to and extends axially out from the forward bulkhead. The outer radial combustor wall is attached to and extends axially out from the forward bulkhead. At least one of the inner radial combustor wall and the outer radial combustor wall includes a plurality of quench aperture sets. Each quench aperture set includes a plurality of quench apertures. Adjacent quench apertures included within each quench aperture set are separated by an intraset distance. Adjacent quench aperture sets are separated by an interset distance. The intraset distance is different than the interset distance. The outer radial combustor wall is disposed radially outside the inner radial combustor wall, thereby defining an annular combustion region therebetween.
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4.发明公开Temperature mixing enhancement with locally co-swirling quench jet pattern for gas turbine engine combustor 审中-公开Temperaturmischverbesserung mit lokalem Wirbelstrahlmusterfürein Gasturbinenbrenner
公开(公告)号：EP2551594A3
公开(公告)日：2015-05-13
申请号：EP12177888.0
申请日：2012-07-25
IPC分类号： F23R3/06
CPC分类号： F23R3/06 , F23R3/08 , Y02T50/675
摘要： A combustor (56) for a turbine engine (20) includes a first liner (60) defined about an axis (A) with a first row (110) of first combustion air holes (114, 116, 118), one of the fist combustion air holes (114) is defined along each of a multiple of fuel injector zero pitch lines (L1, L2). A second liner (62) defined about the axis (A) with a second row (112) of second combustion air holes (120, 122), each of the second combustion air holes (120, 122) circumferentially offset relative to each of the multiple of fuel injector zero pitch lines (L1, L2).
摘要翻译： 用于涡轮发动机（20）的燃烧器（56）包括围绕具有第一排（110）第一燃烧空气孔（114,116,118）的轴线（A）限定的第一衬套（60），其中一个拳头 燃烧空气孔（114）沿着多个燃料喷射器零间距线（L1，L2）中的每一个限定。 围绕所述轴线（A）限定有第二排（112）第二燃烧空气孔（120,122）的第二衬套（62），所述第二燃烧空气孔（120,122）中的每一个相对于所述第二燃烧空气孔 多个燃料喷射器零间距线（L1，L2）。
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公开(公告)号：EP2551594B1
公开(公告)日：2018-10-10
申请号：EP12177888.0
申请日：2012-07-25
IPC分类号： F23R3/06
CPC分类号： F23R3/06 , F23R3/08 , Y02T50/675
摘要： A combustor (56) for a turbine engine (20) includes a first liner (60) defined about an axis (A) with a first row (110) of first combustion air holes (114, 116, 118), one of the fist combustion air holes (114) is defined along each of a multiple of fuel injector zero pitch lines (L1, L2). A second liner (62) defined about the axis (A) with a second row (112) of second combustion air holes (120, 122), each of the second combustion air holes (120, 122) circumferentially offset relative to each of the multiple of fuel injector zero pitch lines (L1, L2).
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6.发明公开
公开(公告)号：EP2253887A2
公开(公告)日：2010-11-24
申请号：EP10163039.0
申请日：2010-05-17
发明人： Kim, Won-Wook , Snyder, Timothy S.
IPC分类号： F23R3/06
CPC分类号： F23R3/06
摘要： A combustor (20) for a gas turbine engine includes a forward bulkhead (22), an inner radial combustor wall (26) and an outer radial combustor wall (28). The forward bulkhead has a plurality of circumferentially disposed injector apertures (34). The inner radial combustor wall is attached to and extends axially out from the forward bulkhead. The outer radial combustor wall is attached to and extends axially out from the forward bulkhead. At least one of the inner radial combustor wall and the outer radial combustor wall includes a plurality of quench aperture sets. Each quench aperture set includes a plurality of quench apertures. Adjacent quench apertures included within each quench aperture set are separated by an intraset distance. Adjacent quench aperture sets are separated by an interset distance. The intraset distance is different than the interset distance. The outer radial combustor wall is disposed radially outside the inner radial combustor wall, thereby defining an annular combustion region therebetween.
摘要翻译： 用于燃气涡轮发动机的燃烧器（20）包括前舱壁（22），内径向燃烧器壁（26）和外径向燃烧室壁（28）。 前隔板具有多个周向设置的喷射孔（34）。 内部径向燃烧器壁从前舱壁附接到轴向外延伸。 外部径向燃烧器壁从前舱壁附接到轴向外延伸。 内径向燃烧器壁和外径向燃烧器壁中的至少一个包括多个淬火孔组。 每个淬火孔径组包括多个淬火孔。 每个淬火孔径组件中包括的相邻淬火孔径由一个入口间距离分开。 相邻的淬火孔径组间隔一个间距。 内部距离不同于间距。 外径向燃烧室壁径向设置在内径向燃烧室壁的外侧，从而在其间形成环形燃烧区域。
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7.发明公开Gas turbine combustor with improved quench holes arrangement 审中-公开Gasturbinenbrennkammer mit verbesserter Anordnung vonLöschlöchern
公开(公告)号：EP2290289A2
公开(公告)日：2011-03-02
申请号：EP10251531.9
申请日：2010-08-31
发明人： Snyder, Timothy S. , Kim, Won-Wook
CPC分类号： F23R3/06 , F23R3/50 , Y02T50/675
摘要： A gas turbine engine has a combustor module including an annular combustor (26) having a liner assembly that defines an annular combustion chamber (30) and includes a circumferential row of a plurality of relatively large combustion dilution air admission holes (116) and a circumferential row of a plurality of smaller quench air admission holes (120) disposed downstream with respect to the flow of combustion gas products. The plurality of quench air admission holes (120) are arranged with respect to the plurality of relatively large dilution air admission holes (116) disposed upstream thereof such that there is associated with each dilution air admission hole (116) a first quench air admission hole (120) and a second quench air admission hole (120), the first quench air admission hole (120) being offset laterally in a first lateral direction and the second quench air admission hole (120) being offset laterally in a second lateral direction opposite to the first direction.
摘要翻译： 燃气涡轮发动机具有燃烧器模块，该燃烧器模块包括环形燃烧器（26），该环形燃烧器具有限定环形燃烧室（30）的衬套组件，并且包括周向排的多个相对大的燃烧稀释空气进入孔（116） 多个更小的骤冷空气入口孔（120）相对于燃烧气体产物的流动设置在下游。 多个骤冷空气入口孔相对于设置在其上游的多个相对较大的稀释空气进入孔（116）布置，使得与每个稀释空气入口孔（116）相关联，第一骤冷空气入口孔 （120）和第二骤冷气体入口孔（120），所述第一骤冷空气进入孔（120）在第一横向方向上横向偏移，所述第二骤冷空气入口孔（120）在相反的第二横向方向上横向偏移 到第一个方向。
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8.发明公开Temperature mixing enhancement with locally co-swirling quench jet pattern for gas turbine engine combustor 审中-公开与用于燃气涡轮机燃烧器本地涡旋光束图案温度下混合的改进
公开(公告)号：EP2551594A2
公开(公告)日：2013-01-30
申请号：EP12177888.0
申请日：2012-07-25
IPC分类号： F23R3/06
CPC分类号： F23R3/06 , F23R3/08 , Y02T50/675
摘要： A combustor (56) for a turbine engine (20) includes a first liner (60) defined about an axis (A) with a first row (110) of first combustion air holes (114, 116, 118), one of the fist combustion air holes (114) is defined along each of a multiple of fuel injector zero pitch lines (L1, L2). A second liner (62) defined about the axis (A) with a second row (112) of second combustion air holes (120, 122), each of the second combustion air holes (120, 122) circumferentially offset relative to each of the multiple of fuel injector zero pitch lines (L1, L2).
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