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公开(公告)号：US08959888B2
公开(公告)日：2015-02-24
申请号：US13305120
申请日：2011-11-28
摘要： An emissions control system for a gas turbine engine including a flow-directing structure (24) that delivers combustion gases (22) from a burner (32) to a turbine. The emissions control system includes: a conduit (48) configured to establish fluid communication between compressed air (22) and the combustion gases within the flow-directing structure (24). The compressed air (22) is disposed at a location upstream of a combustor head-end and exhibits an intermediate static pressure less than a static pressure of the combustion gases within the combustor (14). During operation of the gas turbine engine a pressure difference between the intermediate static pressure and a static pressure of the combustion gases within the flow-directing structure (24) is effective to generate a fluid flow through the conduit (48).
摘要翻译： 一种用于燃气涡轮发动机的排放控制系统，其包括将燃烧气体（22）从燃烧器（32）输送到涡轮机的流动引导结构（24）。 排放物控制系统包括：导管（48），其配置成建立压缩空气（22）与导流结构（24）内的燃烧气体之间的流体连通。 压缩空气（22）设置在燃烧器头端的上游位置处，并且具有小于燃烧器（14）内的燃烧气体的静压力的中间静压力。 在燃气涡轮发动机的操作期间，导流结构（24）内的中间静压与燃烧气体的静压之间的压力差有效地产生通过导管（48）的流体流。
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公开(公告)号：US20130133330A1
公开(公告)日：2013-05-30
申请号：US13305120
申请日：2011-11-28
IPC分类号： F23R3/42
摘要： An emissions control system for a gas turbine engine including a flow-directing structure (24) that delivers combustion gases (22) from a burner (32) to a turbine. The emissions control system includes: a conduit (48) configured to establish fluid communication between compressed air (22) and the combustion gases within the flow-directing structure (24). The compressed air (22) is disposed at a location upstream of a combustor head-end and exhibits an intermediate static pressure less than a static pressure of the combustion gases within the combustor (14). During operation of the gas turbine engine a pressure difference between the intermediate static pressure and a static pressure of the combustion gases within the flow-directing structure (24) is effective to generate a fluid flow through the conduit (48).
摘要翻译： 一种用于燃气涡轮发动机的排放控制系统，其包括将燃烧气体（22）从燃烧器（32）输送到涡轮机的流动引导结构（24）。 排放物控制系统包括：导管（48），其配置成建立压缩空气（22）与导流结构（24）内的燃烧气体之间的流体连通。 压缩空气（22）设置在燃烧器头端的上游位置处，并且具有小于燃烧器（14）内的燃烧气体的静压力的中间静压力。 在燃气涡轮发动机的操作期间，导流结构（24）内的中间静压与燃烧气体的静压之间的压力差有效地产生通过导管（48）的流体流。
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公开(公告)号：US09353949B2
公开(公告)日：2016-05-31
申请号：US13448458
申请日：2012-04-17
申请人： Walter R. Laster , Reinhard Schilp
发明人： Walter R. Laster , Reinhard Schilp
CPC分类号： F23R3/10 , F01D17/141 , F01D17/162 , F01D17/165 , F02C9/20 , F23R3/14 , F23R3/26
摘要： A flow conditioning device (30, 50, 70, 100, 150) for a can annular gas turbine engine, including a plurality of flow elements (32, 34, 52, 54, 72, 74, 102) disposed in a compressed air flow path (42, 60, 80, 114, 122) leading to a combustor (12), configured such that relative adjustment of at least one flow directing element (32, 52, 72, 110) with respect to an adjacent flow directing element (34, 54, 74, 112, 120) during operation of the gas turbine engine is effective to adjust a level of choking of the compressed air flow path (42, 60, 80, 114, 122).
摘要翻译： 一种用于罐式环形燃气涡轮发动机的流量调节装置（30,50,70,100,150），包括设置在压缩空气流中的多个流动元件（32,34,52,54,72,74,102） 通向燃烧器（12）的路径（42,60,80,114,122），其被配置为使得至少一个流动引导元件（32,52,72,110）相对于相邻的流动引导元件（ 34,54,74,112,120）在燃气涡轮发动机的运行期间有效地调节压缩空气流路（42,60,80,114,122）的阻塞水平。
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公开(公告)号：US20150369135A1
公开(公告)日：2015-12-24
申请号：US13448458
申请日：2012-04-17
申请人： Walter R. Laster , Reinhard Schilp
发明人： Walter R. Laster , Reinhard Schilp
CPC分类号： F23R3/10 , F01D17/141 , F01D17/162 , F01D17/165 , F02C9/20 , F23R3/14 , F23R3/26
摘要： A flow conditioning device (30, 50, 70, 100, 150) for a can annular gas turbine engine, including a plurality of flow elements (32, 34, 52, 54, 72, 74, 102) disposed in a compressed air flow path (42, 60, 80, 114, 122) leading to a combustor (12), configured such that relative adjustment of at least one flow directing element (32, 52, 72, 110) with respect to an adjacent flow directing element (34, 54, 74, 112, 120) during operation of the gas turbine engine is effective to adjust a level of choking of the compressed air flow path (42, 60, 80, 114, 122).
摘要翻译： 一种用于罐式环形燃气涡轮发动机的流量调节装置（30,50,70,100,150），包括设置在压缩空气流中的多个流动元件（32,34,52,54,72,74,102） 通向燃烧器（12）的路径（42,60,80,114,122），其被配置为使得至少一个流动引导元件（32,52,72,110）相对于相邻的流动引导元件（ 34,54,74,112,120）在燃气涡轮发动机的运行期间有效地调节压缩空气流路（42,60,80,114,122）的阻塞水平。
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5.发明授权Mid-section of a can-annular gas turbine engine with an improved rotation of air flow from the compressor to the turbine 有权具有改进的从压缩机到涡轮机的空气流的旋转的罐环式燃气涡轮发动机的中部公开(公告)号：US09291063B2
公开(公告)日：2016-03-22
申请号：US13408287
申请日：2012-02-29
摘要： A midframe portion (313) of a gas turbine engine (310) is presented and includes a compressor section with a last stage blade to orient an air flow (311) at a first angle (372). The midframe portion (313) further includes a turbine section with a first stage blade to receive the air flow (311) oriented at a second angle (374). The midframe portion (313) further includes a manifold (314) to directly couple the air flow (311) from the compressor section to a combustor head (318) upstream of the turbine section. The combustor head (318) introduces an offset angle in the air flow (311) from the first angle (372) to the second angle (374) to discharge the air flow (311) from the combustor head (318) at the second angle (374). While introducing the offset angle, the combustor head (318) at least maintains or augments the first angle (372).
摘要翻译： 呈现燃气涡轮发动机（310）的中架部分（313）并且包括具有最后级叶片的压缩机部分，以使空气流（311）以第一角度（372）定向。 中间部分（313）还包括具有第一级叶片的涡轮机部分，以接收以第二角度（374）定向的空气流（311）。 中间部分（313）还包括歧管（314），用于将空气流（311）从压缩机部分直接耦合到涡轮部分上游的燃烧器头部（318）。 燃烧器头部（318）将空气流（311）中的偏移角从第一角度（372）引入第二角度（374），以使空气流（311）以第二角度从燃烧器头部（318）排出 （374）。 在引入偏移角的同时，燃烧器头（318）至少保持或增加第一角度（372）。
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公开(公告)号：US08257035B2
公开(公告)日：2012-09-04
申请号：US11950810
申请日：2007-12-05
申请人： Reinhard Schilp
发明人： Reinhard Schilp
IPC分类号： F03B3/18
摘要： A turbine vane for a gas turbine engine having an outer wall of non-uniform thickness. The turbine vane may be formed from a generally elongated airfoil formed from an outer wall having a leading edge, a trailing edge, a pressure side, a suction side, a first endwall at a first end, a second endwall at a second end opposite the first end, and an internal cooling system positioned internally of the outer wall. The outer wall may be formed of a non-uniform thickness such that aspects of the outer wall positioned between an outboardmost portion of the outer wall and an inboardmost portion of the outer wall are thinner than the outboardmost and inboardmost portions of the outer wall.
摘要翻译： 一种用于具有不均匀厚度的外壁的燃气涡轮发动机的涡轮叶片。 涡轮叶片可以由大体细长的翼型形成，该翼面由外壁形成，该外壁具有前缘，后缘，压力侧，吸力侧，第一端的第一端壁，与第二端相对的第二端的第二端壁 第一端和位于外壁内部的内部冷却系统。 外壁可以由不均匀的厚度形成，使得位于外壁的外侧部分和外壁的最内部之间的外壁的方面比外壁的外侧和最外侧部分更薄。
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7.发明授权Air regulation for film cooling and emission control of combustion gas structure 有权燃烧气体结构薄膜冷却和排放控制的空气调节公开(公告)号：US09181813B2
公开(公告)日：2015-11-10
申请号：US13541841
申请日：2012-07-05
申请人： Reinhard Schilp
发明人： Reinhard Schilp
摘要： A gas turbine engine compressed air flow control arrangement, including: a combustion gas structure having an acceleration geometry (20) configured to receive combustion gas (18) from a can combustor and accelerate the combustion gas (18) to a speed appropriate for delivery onto a first row of turbine blades, the combustion gas structure defining a straight combustion flow path; a film cooling hole (58) disposed through the combustion gas structure at a location within or downstream of the acceleration geometry (20); a sleeve (64) surrounding at least a portion of the combustion gas structure comprising the film cooling hole and defining a volume (62) between the combustion gas structure and the sleeve (64); and an adjustable flow control system configured to adjust a flow volume between the plenum (44) and the volume (62).
摘要翻译： 一种燃气涡轮发动机压缩空气流量控制装置，包括：具有加速几何形状（20）的燃烧气体结构，其构造成从罐燃烧器接收燃烧气体（18），并将燃烧气体（18）加速到适于输送到 第一排涡轮叶片，燃烧气体结构限定直燃燃烧流路; 在所述加速几何形状（20）内或下游的位置处设置穿过所述燃烧气体结构的薄膜冷却孔（58）。 围绕包括所述薄膜冷却孔并且限定所述燃烧气体结构和所述套筒（64）之间的体积（62）的所述燃烧气体结构的至少一部分的套筒（64）。 以及可调节流量控制系统，其被配置为调节所述增压室（44）和所述容积（62）之间的流量。
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8.发明申请AIR REGULATION FOR FILM COOLING AND EMISSION CONTROL OF COMBUSTION GAS STRUCTURE 有权燃气结构的电磁冷却和排放控制的空气调节公开(公告)号：US20140338304A1
公开(公告)日：2014-11-20
申请号：US13541841
申请日：2012-07-05
申请人： Reinhard Schilp
发明人： Reinhard Schilp
IPC分类号： F02C7/057
摘要： A gas turbine engine compressed air flow control arrangement, including: a combustion gas structure having an acceleration geometry (20) configured to receive combustion gas (18) from a can combustor and accelerate the combustion gas (18) to a speed appropriate for delivery onto a first row of turbine blades, the combustion gas structure defining a straight combustion flow path; a film cooling hole (58) disposed through the combustion gas structure at a location within or downstream of the acceleration geometry (20); a sleeve (64) surrounding at least a portion of the combustion gas structure comprising the film cooling hole and defining a volume (62) between the combustion gas structure and the sleeve (64); and an adjustable flow control system configured to adjust a flow volume between the plenum (44) and the volume (62).
摘要翻译： 一种燃气涡轮发动机压缩空气流量控制装置，包括：具有加速几何形状（20）的燃烧气体结构，其被构造成从罐燃烧器接收燃烧气体（18），并将燃烧气体（18）加速到适于输送到 第一排涡轮叶片，燃烧气体结构限定直燃燃烧流路; 在所述加速几何形状（20）内或下游的位置处设置穿过所述燃烧气体结构的薄膜冷却孔（58）。 围绕包括所述薄膜冷却孔并且限定所述燃烧气体结构和所述套筒（64）之间的体积（62）的所述燃烧气体结构的至少一部分的套筒（64）。 以及可调节流量控制系统，其被配置为调节所述增压室（44）和所述容积（62）之间的流量。
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公开(公告)号：US20130055720A1
公开(公告)日：2013-03-07
申请号：US13226529
申请日：2011-09-07
申请人： TIMOTHY A. FOX , Reinhard Schilp
发明人： TIMOTHY A. FOX , Reinhard Schilp
IPC分类号： F02C7/22
摘要： A gas turbine combustor assembly including a combustor liner and a plurality of fuel nozzle assemblies arranged in an annular array extending within the combustor liner. The fuel nozzle assemblies each include fuel nozzle body integral with a swirler assembly, and the swirler assemblies each a bellmouth structure to turn air radially inwardly for passage into the swirler assemblies. A radially outer removed portion of each of the bellmouth structures define a periphery diameter spaced from an inner surface of the combustor liner, and an interface ring is provided extending between the combustor liner and the removed portions of the bellmouth structures at the periphery diameter.
摘要翻译： 一种燃气轮机燃烧器组件，包括燃烧器衬套和布置成在燃烧器衬套内延伸的环形阵列的多个燃料喷嘴组件。 燃料喷嘴组件各自包括与旋流器组件一体的燃料喷嘴体，并且旋流器组件各自具有喇叭口结构，以将空气径向向内转动以通过旋流器组件。 每个喇叭口结构的径向外部去除部分限定了与燃烧器衬套的内表面间隔开的周向直径，并且设置在燃烧器衬套和鼓形结构的外围直径的去除部分之间延伸的界面环。
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公开(公告)号：US20150020498A1
公开(公告)日：2015-01-22
申请号：US13945983
申请日：2013-07-19
申请人： Reinhard Schilp
发明人： Reinhard Schilp
CPC分类号： F02C7/12 , F01D9/023 , F05D2260/963 , F23R3/002 , F23R2900/00014
摘要： A cover (54, 54A-B) enclosing with clearance (65) an acoustic damping resonator (24) on a working gas path liner (22) of a gas turbine component (28). The cover includes a coolant inlet chamber (56, 56B) with a top wall (58, 58B) that is closer to the liner than a top wall (32) of the resonator, and extends upstream from the resonator relative to the working gas flow (48). Compressed air (26) surrounds the cover at a higher pressure than the working gas and flows (44) into and through the coolant inlet chamber, then through holes (34) in the resonator, then exits through holes (38) the liner into the working gas. The coolant inlet chamber directs the flow of compressed air over a weld (50) of the upstream wall (40) of the resonator to cool it. The cover may be formed as a box (57) or a sleeve (69).
摘要翻译： 在燃气轮机部件（28）的工作气体通道衬套（22）上包围有间隙（65）的声阻尼谐振器（24）的盖（54,5A-B）。 所述盖包括具有顶壁（58,58B）的冷却剂入口室（58,58B），所述顶壁（58,58B）比所述谐振器的顶壁（32）更靠近所述衬套，并且相对于所述工作气体流在所述谐振器的上游延伸 （48）。 压缩空气（26）在比工作气体高的压力下围绕盖并且流入（44）进入冷却剂入口室，然后通过谐振器中的通孔（34），然后通过孔（38）将衬管排出到 工作气体 冷却剂入口室将压缩空气流引导到谐振器的上游壁（40）的焊缝（50）上以使其冷却。 盖可以形成为盒（57）或套（69）。
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