-
公开(公告)号：US08387358B2
公开(公告)日：2013-03-05
申请号：US12696241
申请日：2010-01-29
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：US20110185699A1
公开(公告)日：2011-08-04
申请号：US12696241
申请日：2010-01-29
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。
-
3.发明授权Gas turbine engine combustor circumferential acoustic reduction using flame temperature nonuniformities 有权燃气轮机发动机燃烧器采用周边声学还原使用火焰温度不均匀性公开(公告)号：US08631656B2
公开(公告)日：2014-01-21
申请号：US12059256
申请日：2008-03-31
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。
-
4.发明申请GAS TURBINE ENGINE COMBUSTOR CIRCUMFERENTIAL ACOUSTIC REDUCTION USING FLAME TEMPERATURE NONUNIFORMITIES 有权气体涡轮发动机燃烧器使用火焰温度非均匀性进行循环减震公开(公告)号：US20090241548A1
公开(公告)日：2009-10-01
申请号：US12059256
申请日：2008-03-31
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。
-
公开(公告)号：US6141967A
公开(公告)日：2000-11-07
申请号：US5343
申请日：1998-01-09
申请人： Paul R. Angel , James M. Caldwell , Narendra D. Joshi , Steven Marakovits , Kelley A. Foresman , Steven G. Goebel , Richard E. Warren, Jr.
发明人： Paul R. Angel , James M. Caldwell , Narendra D. Joshi , Steven Marakovits , Kelley A. Foresman , Steven G. Goebel , Richard E. Warren, Jr.
摘要： An apparatus for premixing fuel and air prior to combustion in a gas turbine engine, including: a linear mixing duct having a circular cross-section defined by a wall; a centerbody located along a central axis of the mixing duct and extending substantially the full length of the mixing duct, the centerbody having a plurality of orifices therein to inject fuel into the mixing duct with an axial velocity component; a fuel supply in flow communication with the centerbody orifices; an outer annular swirler located adjacent an upstream end of the mixing duct and including a plurality of circumferentially spaced vanes oriented so as to swirl air flowing therethrough in a first direction; an inner annular swirler located adjacent the mixing duct upstream end and including a plurality of circumferentially spaced vanes, the vanes having an outer radial portion having a leading edge and a trailing edge oriented so as to swirl air flowing therethrough in a second direction opposite the first swirl direction by the outer annular swirler vanes and an inner radial portion with a leading edge and a trailing edge oriented so as to provide a boundary layer of air substantially along the centerbody; and, a hub separating the inner and outer annular swirlers to permit independent rotation of an air stream therethrough. The outer annular swirler may also include vanes having an inner radial portion with a leading edge and a trailing edge oriented so as to swirl the air flow therethrough and an outer radial portion having a leading edge and a trailing edge oriented so as to provide a boundary layer of air substantially along the mixing duct wall. High pressure air is injected from a compressor into the mixing duct through the inner and outer annular swirlers and fuel is injected into the mixing duct so that the high pressure air and the fuel is uniformly mixed therein, whereby minimal formation of pollutants is produced when the fuel/air mixture is exhausted out the downstream end of the mixing duct into a combustor and ignited.
-
公开(公告)号：US06758045B2
公开(公告)日：2004-07-06
申请号：US10233356
申请日：2002-08-30
IPC分类号： F02C314
CPC分类号： F23R3/002 , F23R3/346 , F23R3/50 , F23R2900/00005
摘要： A method enables a gas turbine engine multi-domed combustor including an outer liner and an inner liner that define a combustion chamber therebetween to be assembled. The method comprises coupling a first dome including a heat shield that includes an annular endbody that extends a first distance axially from the heat shield to the combustor outer liner, and coupling a second dome including a heat shield that includes an annular endbody that extends a second distance axially from the heat shield to the first dome, such that the second dome is radially aligned with respect to the first dome, and wherein the second dome second distance is less than the first dome first distance.
摘要翻译： 一种方法能够使燃气涡轮发动机多圆顶燃烧器包括在其间限定燃烧室以组装的外衬套和内衬套。 该方法包括联接包括隔热罩的第一穹顶，所述隔热罩包括环形端体，所述环形端体从所述隔热罩轴向延伸到所述燃烧器外衬套，并且连接包括隔热罩的第二穹顶，所述隔热罩包括环形端体， 从隔热板轴向延伸到第一圆顶，使得第二圆顶相对于第一圆顶径向对准，并且其中第二圆顶第二距离小于第一圆顶第一距离。
-
-
-
-
-
搜索结果
6 条记录 (耗时 0.019 秒)
