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41.发明申请SYSTEM FOR CONTROLLING A FLOW RATE OF A COMPRESSED WORKING FLUID TO A COMBUSTOR FUEL INJECTOR 有权用于控制压缩工作流体到燃烧器燃料喷射器的流量的系统公开(公告)号：US20140260264A1
公开(公告)日：2014-09-18
申请号：US13845397
申请日：2013-03-18
IPC分类号： F02C7/22
摘要： A system for controlling air flow rate of a compressed working fluid to a fuel injector of a combustor includes an outer casing that defines a high pressure plenum around a portion of the combustor, an extraction port in fluid communication with the high pressure plenum and an inlet port. The combustor includes a plurality of fuel injectors arranged around a combustion liner, an inner flow sleeve, an outer air shield that surrounds the plurality of fuel injectors and the inner flow sleeve. The outer air shield defines an injection an air plenum between the outer air shield and the inner flow sleeve and an inlet to the injection air plenum. An external fluid circuit provides fluid communication between the extraction port and the inlet port. A baffle extends between the outer casing and the outer air shield to provide flow separation between the inlet and the high pressure plenum.
摘要翻译： 用于控制压缩工作流体对燃烧器的燃料喷射器的空气流量的系统包括：外壳，其围绕燃烧器的一部分限定高压增压室;与高压气室流体连通的抽出口和入口 港口。 燃烧器包括围绕燃烧衬套布置的多个燃料喷射器，内部流动套筒，围绕多个燃料喷射器和内部流动套筒的外部空气屏蔽件。 外部空气屏蔽件限定了在外部空气屏蔽和内部流动套筒之间的注入空气增压室和注入空气增压室的入口。 外部流体回路在提取口和入口之间提供流体连通。 挡板在外壳和外部空气屏蔽之间延伸，以提供入口和高压集气室之间的流动分离。
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公开(公告)号：US20140144145A1
公开(公告)日：2014-05-29
申请号：US14001367
申请日：2012-02-22
申请人： Leif Rackwitz , Emmanuel Aurifeille
发明人： Leif Rackwitz , Emmanuel Aurifeille
IPC分类号： F23R3/02
CPC分类号： F23R3/02 , F23R3/045 , F23R3/06 , Y02T50/675
摘要： The present invention relates to a gas-turbine combustion chamber with an outer combustion chamber wall concentric to a gas-turbine center axis and with an inner combustion chamber wall, with several burners arranged spread over the circumference of the combustion chamber, and with air inlet recesses which in at least one radial plane are provided spread over the circumference on an outer combustion chamber wall and on an inner combustion chamber wall, where the burner is designed to form a flow provided with a swirl and where air inlet recesses assigned to a burner are dimensioned in differing size in order to generate airflows of differing size, characterized in that at least one of the respective air inlet recesses is designed for supplying air in the flow direction of the swirl of the combustion chamber flow and is provided with flow guidance walls.
摘要翻译： 本发明涉及一种燃气轮机燃烧室，其具有与燃气涡轮机中心轴线同心的外部燃烧室壁和内部燃烧室壁，多个燃烧器布置在燃烧室的圆周上，并且具有空气入口 在至少一个径向平面中设置的凹部在外部燃烧室壁和内部燃烧室壁上在圆周上分布，其中燃烧器被设计成形成设置有涡流的流，并且其中分配给燃烧器的空气入口凹部 尺寸为不同的尺寸以便产生不同尺寸的气流，其特征在于，相应空气入口凹陷中的至少一个被设计用于在燃烧室流动的涡流的流动方向上供应空气，并且设有流动引导壁 。
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公开(公告)号：US20130283814A1
公开(公告)日：2013-10-31
申请号：US13456185
申请日：2012-04-25
CPC分类号： F01D25/14 , F05D2260/201 , F23R3/045 , F23R2900/03042
摘要： A system includes a turbine. The turbine includes a rotor, a stator, and a cooling insert. The rotor includes multiple turbine blades. The stator surrounds the rotor and includes an inner wall surrounding the multiple turbine blades, an outer wall surrounding the inner wall, and a cooling chamber between the inner wall and the outer wall. The cooling insert extends through an opening in the outer wall into the cooling chamber. The insert includes a side wall extending around an axis, an end wall crosswise to the axis, a set of lateral ports extending through the side wall, and end ports extending through the end wall. The cooling insert is configured to direct a cooling fluid through the set of lateral ports and end ports into the cooling chamber.
摘要翻译： 一种系统包括涡轮机。 涡轮机包括转子，定子和冷却插入件。 转子包括多个涡轮叶片。 定子围绕转子并且包括围绕多个涡轮机叶片的内壁，围绕内壁的外壁以及在内壁和外壁之间的冷却室。 冷却插件延伸穿过外壁中的开口进入冷却室。 插入件包括围绕轴线延伸的侧壁，与轴线交叉的端壁，延伸穿过侧壁的一组侧向端口和延伸穿过端壁的端部端口。 冷却插入件构造成将冷却流体引导通过该组侧向端口和端部端口进入冷却室。
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公开(公告)号：US20130283806A1
公开(公告)日：2013-10-31
申请号：US13456602
申请日：2012-04-26
申请人： James Christopher Monaghan , Thomas Edward Johnson , Johnie F. McConnaughhay , Heath Michael Ostebee
发明人： James Christopher Monaghan , Thomas Edward Johnson , Johnie F. McConnaughhay , Heath Michael Ostebee
CPC分类号： F23R3/045 , F23R3/06 , F23R2900/00017 , F23R2900/00019 , Y10T29/49346
摘要： A combustor generally includes a liner that at least partially defines a combustion chamber within the combustor. The liner may generally include a hole that extends through the liner and that at least partially defines a mating surface. An insert having an outer surface extends at least partially through the hole. A projection that at least partially defines a mating surface at least partially circumferentially surrounds the insert outer surface. A joint between the projection mating surface and the hole mating surface provides a connection point between the projection mating surface and the liner hole mating surface.
摘要翻译： 燃烧器通常包括至少部分地限定燃烧器内的燃烧室的衬套。 衬里通常可以包括延伸穿过衬套并且至少部分地限定配合表面的孔。 具有外表面的插入件至少部分延伸穿过孔。 至少部分地限定配合表面的突起至少部分地圆周地包围插入物外表面。 突起配合表面和孔匹配表面之间的接头提供了突出配合表面和衬套孔配合表面之间的连接点。
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公开(公告)号：US20130167547A1
公开(公告)日：2013-07-04
申请号：US13342587
申请日：2012-01-03
IPC分类号： F23R3/26
摘要： According to one aspect of the invention, a gas turbine engine includes a combustor, a fuel nozzle placed in an end of the combustor, and a passage configured to receive an air flow from a compressor discharge casing, wherein the passage directs the air flow into a chamber downstream of the nozzle, wherein a chamber pressure is lower than a compressor discharge casing pressure. The gas turbine engine also includes a flow control device configured to control the air flow from the compressor discharge casing into the passage.
摘要翻译： 根据本发明的一个方面，一种燃气涡轮发动机包括燃烧器，设置在燃烧器的端部的燃料喷嘴，以及构造成接收来自压缩机排出壳体的空气流的通道，其中通道将气流引导到 在喷嘴下游的腔室，其中室压力低于压缩机排气套管压力。 燃气涡轮发动机还包括流量控制装置，该流量控制装置被配置为控制从压缩机排放壳体进入通道的空气流。
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公开(公告)号：US20130045450A1
公开(公告)日：2013-02-21
申请号：US13213460
申请日：2011-08-19
申请人： Jong Ho Uhm , Willy Steve Ziminsky , Thomas Edward Johnson , Shiva Srinivasan , William David York
发明人： Jong Ho Uhm , Willy Steve Ziminsky , Thomas Edward Johnson , Shiva Srinivasan , William David York
IPC分类号： F23D5/00
摘要： A system for reducing combustion dynamics in a combustor includes an end cap that extends radially across the combustor and includes an upstream surface axially separated from a downstream surface. A combustion chamber is downstream of the end cap, and tubes extend from the upstream surface through the downstream surface. Each tube provides fluid communication through the end cap to the combustion chamber. The system further includes means for reducing combustion dynamics in the combustor. A method for reducing combustion dynamics in a combustor includes flowing a working fluid through tubes that extend axially through an end cap that extends radially across the combustor and obstructing at least a portion of the working fluid flowing through a first set of the tubes.
摘要翻译： 用于减少燃烧器中的燃烧动力学的系统包括：端盖，其径向延伸穿过燃烧器并且包括与下游表面轴向分离的上游表面。 燃烧室在端盖的下游，并且管从上游表面延伸穿过下游表面。 每个管提供通过端盖到燃烧室的流体连通。 该系统还包括用于减少燃烧器中的燃烧动力学的装置。 用于减少燃烧器中的燃烧动力学的方法包括使工作流体通过管轴流动，所述管道轴向延伸穿过径向延伸穿过燃烧器的端盖，并阻塞流过第一组管的至少一部分工作流体。
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47.发明申请ASSEMBLIES AND APPARATUS RELATED TO INTEGRATING LATE LEAN INJECTION INTO COMBUSTION TURBINE ENGINES 有权集成和装置相关的整体升级注入燃油涡轮发动机公开(公告)号：US20130031906A1
公开(公告)日：2013-02-07
申请号：US13204340
申请日：2011-08-05
IPC分类号： F23R3/42
摘要： An assembly for use in a late lean injection system of a combustor of a combustion turbine engine, wherein the combustor includes an inner radial wall, which defines a primary combustion chamber downstream of a primary fuel nozzle, and an outer radial wall, which surrounds the inner radial wall forming a flow annulus therebetween, the assembly comprising: a boss rigidly secured to the inner radial wall, the boss being configured to define a hollow passageway through the inner radial wall; a transfer tube slideably engaged within the boss; a stop formed on the transfer tube; and damping means positioned between the boss and the stop.
摘要翻译： 一种用于燃气涡轮发动机的燃烧器的后期稀注射系统的组件，其中所述燃烧器包括限定主燃料喷嘴下游的主燃烧室的内径向壁，以及外径向壁围绕 所述内部径向壁在其间形成流动环空，所述组件包括：刚性地固定到所述内部径向壁的凸台，所述凸起构造成限定通过所述内部径向壁的中空通道; 转移管可滑动地接合在所述凸台内; 形成在转移管上的止动件; 以及位于凸台和止挡件之间的阻尼装置。
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公开(公告)号：US20120067051A1
公开(公告)日：2012-03-22
申请号：US12976092
申请日：2010-12-22
申请人： Victor L. Oechsle
发明人： Victor L. Oechsle
IPC分类号： F02C7/22
CPC分类号： F02C3/16 , F02C3/14 , F05D2240/127 , F23R3/045 , F23R3/16 , F23R3/38 , F23R3/44 , F23R2900/00015 , F23R2900/03282
摘要： The present invention provides in one embodiment a unique gas turbine engine. Another embodiment is a unique gas turbine engine combustion system. Still another embodiment is a unique gas turbine engine combustor. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for gas turbine engines and gas turbine engine combustion systems and combustors.
摘要翻译： 本发明在一个实施例中提供了独特的燃气涡轮发动机。 另一个实施例是独特的燃气涡轮发动机燃烧系统。 另一个实施例是独特的燃气涡轮发动机燃烧器。 其他实施例包括用于燃气涡轮发动机和燃气涡轮发动机燃烧系统和燃烧器的装置，系统，装置，硬件，方法和组合。
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公开(公告)号：US20100218504A1
公开(公告)日：2010-09-02
申请号：US12394725
申请日：2009-02-27
CPC分类号： F23R3/045 , F23R3/50 , Y02T50/675
摘要： A combustor may include an outer liner having a first group of air admission holes and defining a plurality of outer liner regions. The combustor may further include an inner liner having a second group of air admission holes and defining a plurality of inner liner regions. The first group of air admission holes within a respective outer liner region may include a first plunged air admission hole approximately axially aligned with the respective fuel injector, a second plunged air admission hole approximately on the outer boundary line between the respective outer liner region and a first adjacent outer liner region, the first air admission hole being downstream of the second air admission hole, and a third plunged air admission hole approximately on the outer boundary line between the respective outer liner region and a second adjacent outer liner region.
摘要翻译： 燃烧器可以包括具有第一组进气孔并且限定多个外衬里区域的外衬套。 燃烧器还可以包括具有第二组进气孔并限定多个内衬区域的内衬。 在相应的外衬里区域内的第一组进气孔可以包括大致与相应的燃料喷射器轴向对准的第一入口进气孔，大致在相应的外衬里区域和相应的外衬里区域之间的外边界线上的第二穿入空气进入孔 第一相邻的外衬垫区域，第一进气孔位于第二进气孔的下游，第三入口孔大致在相应的外衬垫区域和第二相邻的外衬里区域之间的外边界线上。
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公开(公告)号：US07052231B2
公开(公告)日：2006-05-30
申请号：US10424440
申请日：2003-04-28
IPC分类号： F01D5/14
CPC分类号： F01D11/24 , F23R3/045 , Y02T50/675
摘要： A method enables a nozzle support for a gas turbine engine to be fabricated. The method comprises forming an annular assembly including a plurality of circumferentially-spaced gas injector assemblies, wherein each gas injector assembly includes a plenum and a unitarily formed injector that extends outwardly from an outer surface of the plenum, and forming a passageway through the injector such that the passageway extends between an inlet and an outlet, and is obliquely aligned with respect to the plenum exterior surface.
摘要翻译： 一种方法能够制造用于燃气涡轮发动机的喷嘴支架。 该方法包括形成包括多个周向间隔开的气体喷射器组件的环形组件，其中每个气体喷射器组件包括从气室的外表面向外延伸的气室和整体形成的喷射器，并且形成通过喷射器的通道 通道在入口和出口之间延伸，并且相对于增压室外表面倾斜地对准。
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