-
公开(公告)号：US20120186260A1
公开(公告)日：2012-07-26
申请号：US13012838
申请日：2011-01-25
IPC分类号： F01D25/24
CPC分类号： F01D9/023
摘要： An impingement sleeve for a transition piece of a gas turbine is disclosed. The impingement sleeve generally includes a first casing configured to surround a portion of an inner duct of the transition piece and a second casing configured to surround a portion of the inner duct. Additionally, the impingement sleeve may include a joint defined between the first and second casings. The joint may include a plurality of fasteners configured to attach the first casing to the second casing.
摘要翻译： 公开了一种用于燃气轮机的过渡件的冲击套筒。 冲击套管通常包括构造成围绕过渡件的内部管道的一部分的第一壳体和被构造成围绕内部管道的一部分的第二壳体。 此外，冲击套筒可以包括限定在第一和第二壳体之间的接头。 接头可以包括被配置成将第一壳体附接到第二壳体的多个紧固件。
-
公开(公告)号：US20130236301A1
公开(公告)日：2013-09-12
申请号：US13416559
申请日：2012-03-09
申请人： Wei Chen , Stacy Ann Holzman , Keith Cletus Belsom , Ronald James Chila , Richard Martin DiCintio
发明人： Wei Chen , Stacy Ann Holzman , Keith Cletus Belsom , Ronald James Chila , Richard Martin DiCintio
摘要： Disclosed herein are apparatuses and systems for directing the flow of hot gas exiting a transition piece. In an embodiment, an aft frame an aft frame has an exit face that has an airfoil shape. In an embodiment, a transition piece aft exit has an airfoil shape.
摘要翻译： 这里公开了用于引导离开过渡件的热气流的装置和系统。 在一个实施例中，后框架具有具有翼型形状的出口面。 在一个实施例中，过渡件后出口具有翼型形状。
-
公开(公告)号：US20110271688A1
公开(公告)日：2011-11-10
申请号：US12774822
申请日：2010-05-06
IPC分类号： F02C7/20
摘要： A transition piece support for a turbomachine includes one or more support arms extending across a diffuser flowpath to the transition piece. The one or more support arms include a streamwise surface and a crosswise surface. A streamwise extent of the streamwise surface is greater than a crosswise extent of the crosswise surface to reduce flow anomalies in a flow of fluid across the one or more support arms. A turbomachine includes a combustor, a diffuser, a transition piece operably connected to the combustor and a transition piece support including one or more support arms extending across a flow of fluid to the transition piece. The support arms include a streamwise surface and a crosswise surface. A streamwise extent of the streamwise surface is greater than a crosswise extent of the crosswise surface to reduce flow anomalies in a flow of fluid across the one or more support arms.
摘要翻译： 用于涡轮机的过渡件支撑件包括一个或多个支撑臂，跨越扩散器流动路径延伸到过渡件。 一个或多个支撑臂包括流动表面和横向表面。 流动表面的流动范围大于横向表面的横向范围，以减少穿过一个或多个支撑臂的流体流中的流量异常。 涡轮机包括燃烧器，扩散器，可操作地连接到燃烧器的过渡件和过渡件支撑件，该过渡件支撑件包括跨过流体流延伸到过渡件的一个或多个支撑臂。 支撑臂包括流动表面和横向表面。 流动表面的流动范围大于横向表面的横向范围，以减少穿过一个或多个支撑臂的流体流中的流量异常。
-
公开(公告)号：US09249678B2
公开(公告)日：2016-02-02
申请号：US13534744
申请日：2012-06-27
摘要： A transition duct for a combustor of a gas turbine generally includes a transition duct having a frame at an aft end of the transition duct. The frame generally includes a downstream end, a radially outer portion, a radially inner portion opposed to the radially outer portion, a first side portion between the radially outer and inner portions, and a second side portion opposed to the first side portion. A slot in the first side portion of the frame may have a downstream surface adjacent to the downstream end of the frame. A heat shield having an inner surface, an outer surface and a plurality of spacers may extend generally outward from the heat shield inner surface such that the inner surface is adjacent to the slot downstream surface and the frame downstream end.
摘要翻译： 用于燃气涡轮机的燃烧器的过渡管道通常包括在过渡管道的后端具有框架的过渡管道。 框架通常包括下游端，径向外部，与径向外部相对的径向内部，径向外部和内部之间的第一侧部以及与第一侧部相对的第二侧部。 框架的第一侧部分中的槽可以具有与框架的下游端相邻的下游表面。 具有内表面，外表面和多个间隔件的隔热罩可以从隔热罩内表面大致向外延伸，使得内表面邻近槽下游表面和框架下游端。
-
公开(公告)号：US09127552B2
公开(公告)日：2015-09-08
申请号：US13290769
申请日：2011-11-07
摘要： A transition piece aft frame is provided and includes a manifold having an interior that is receptive of fuel and formed to define fuel injection holes configured to inject the received fuel from the manifold interior toward a main flow of products of combustion flowing through the manifold. The manifold includes a main body having an interior facing surface that faces the main flow of the products of the combustion and along which the fuel injection holes are defined.
摘要翻译： 提供过渡件后框架并且包括具有内部的歧管，所述内部可接受燃料并形成以限定燃料喷射孔，所述燃料喷射孔被配置为将所接收的燃料从歧管内部喷射到流过歧管的燃烧产物的主流。 歧管包括主体，其具有面向燃烧产物的主流的内表面，并且燃料喷射孔沿着该主体定义。
-
6.发明授权Assemblies and apparatus related to integrating late lean injection into combustion turbine engines 有权与后期精馏注入燃气涡轮发动机相关的装置和装置公开(公告)号：US09010120B2
公开(公告)日：2015-04-21
申请号：US13204369
申请日：2011-08-05
CPC分类号： F23R3/06 , F23R3/283 , F23R3/346 , F23R3/60 , F23R2900/00012 , F23R2900/00017 , F23R2900/03044
摘要： A transfer tube for use in a late lean injection system of a combustor, 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 outer radial wall including a late lean nozzle, the transfer tube including flow directing structure that defines a fluid passageway. At a first end, the flow directing structure may include an inlet and attachment means that attach the transfer tube to the late lean nozzle. The flow directing structure may have a configuration such that the fluid passageway spans the flow annulus and positions the outlet at a desirable injection point in the inner radial wall.
摘要翻译： 一种用于燃烧器的后期稀薄注射系统的转移管，其中所述燃烧器包括限定主燃料喷嘴下游的初级燃烧室的内部径向壁和围绕形成的内部径向壁的外部径向壁 其间的流动环空，所述外部径向壁包括后倾斜的喷嘴，所述输送管包括限定流体通道的流动引导结构。 在第一端，流动引导结构可以包括将传送管附接到后部稀薄喷嘴的入口和附接装置。 流动引导结构可以具有这样的构造，使得流体通道跨越流动环空并将出口定位在内部径向壁中期望的注入点。
-
7.发明授权Methods relating to integrating late lean injection into combustion turbine engines 有权将后期精益注入集成到燃气涡轮发动机中的方法公开(公告)号：US08407892B2
公开(公告)日：2013-04-02
申请号：US13204306
申请日：2011-08-05
CPC分类号： F23R3/346 , F23R3/06 , F23R3/283 , F23R3/60 , F23R2900/00012 , F23R2900/00017 , F23R2900/00018 , F23R2900/03044 , Y10T29/49316 , Y10T29/4932 , Y10T29/49323 , Y10T29/49348
摘要： The present application thus describes a method of manufacture for a late lean injection system in a combustor of a combustion turbine engine. The method may include the steps of: a) identifying a desired position within the flow assembly for a late lean injector, wherein the late lean injector comprises a late lean nozzle and a transfer tube; b) corresponding to the desired position for the late lean injector, identifying an injection point on the inner radial wall and a late lean nozzle position on the outer radial wall; c) positioning the inner radial wall and the outer radial wall in an unassembled position; d) while in the unassembled position, forming a hole through the inner radial wall at the injection point and slideably engaging the transfer tube within the hole; e) installing the late lean nozzle in the outer radial wall at the late lean nozzle position; f) positioning the inner radial wall and the outer radial wall in an assembled position; and g) connecting the transfer tube to the late lean nozzle.
摘要翻译： 因此，本申请描述了在燃气轮机的燃烧器中用于后期稀薄喷射系统的制造方法。 该方法可以包括以下步骤：a）识别用于后期稀薄注射器的流动组件内的期望位置，其中后期稀释注射器包括后倾斜喷嘴和传送管; b）对应于后期稀薄注射器的期望位置，识别内部径向壁上的注射点和外部径向壁上的后倾斜喷嘴位置; c）将内部径向壁和外部径向壁定位在未组装位置; d）在未组装位置时，在注射点处通过内部径向壁形成孔并且可滑动地接合孔内的传送管; e）在后部稀薄喷嘴位置将后部稀薄喷嘴安装在外径向壁上; f）将内径向壁和外径向壁定位在组装位置; 并且g）将传送管连接到后倾的喷嘴。
-
8.发明申请TURBINE COMPONENT COOLING ARRANGEMENT AND METHOD OF COOLING A TURBINE COMPONENT 审中-公开涡轮组件冷却装置和冷却涡轮机组件的方法公开(公告)号：US20140047846A1
公开(公告)日：2014-02-20
申请号：US13585568
申请日：2012-08-14
CPC分类号： F23R3/04 , F23R2900/03044
摘要： A turbine component cooling arrangement includes a combustor liner defining a combustor chamber, wherein the combustor liner includes an outer surface and an inner surface. Also included is a channel disposed along the outer surface, wherein the channel is configured to receive a cooling flow through at least one aperture extending through a liner ring disposed proximate the outer surface of the combustor liner. Further included is at least one outlet orifice extending between the channel and the combustor chamber through the inner surface for routing the cooling flow along the inner surface within the combustor chamber.
摘要翻译： 涡轮机部件冷却装置包括限定燃烧室的燃烧器衬套，其中燃烧器衬套包括外表面和内表面。 还包括沿着外表面设置的通道，其中通道被配置为接收通过穿过靠近燃烧器衬套的外表面设置的衬套环的至少一个孔的冷却流。 还包括至少一个通过内表面在通道和燃烧器室之间延伸的出口孔，用于沿着燃烧室内的内表面布置冷却流。
-
公开(公告)号：US20140000265A1
公开(公告)日：2014-01-02
申请号：US13534744
申请日：2012-06-27
IPC分类号： F23R3/26
摘要： A transition duct for a combustor of a gas turbine generally includes a transition duct having a frame at an aft end of the transition duct. The frame generally includes a downstream end, a radially outer portion, a radially inner portion opposed to the radially outer portion, a first side portion between the radially outer and inner portions, and a second side portion opposed to the first side portion. A slot in the first side portion of the frame may have a downstream surface adjacent to the downstream end of the frame. A heat shield having an inner surface, an outer surface and a plurality of spacers may extend generally outward from the heat shield inner surface such that the inner surface is adjacent to the slot downstream surface and the frame downstream end.
摘要翻译： 用于燃气涡轮机的燃烧器的过渡管道通常包括在过渡管道的后端具有框架的过渡管道。 框架通常包括下游端，径向外部，与径向外部相对的径向内部，径向外部和内部之间的第一侧部以及与第一侧部相对的第二侧部。 框架的第一侧部分中的槽可以具有与框架的下游端相邻的下游表面。 具有内表面，外表面和多个间隔件的隔热罩可以从隔热罩内表面大致向外延伸，使得内表面邻近槽下游表面和框架下游端。
-
10.发明申请公开(公告)号：US20130272863A1
公开(公告)日：2013-10-17
申请号：US13446718
申请日：2012-04-13
CPC分类号： F01D9/023 , F05D2250/50 , Y10T29/49323
摘要： Disclosed herein are apparatuses, methods, and systems for cross sectional area convergence reduction and selection. In an embodiment, an aft end cross sectional area is determined for a transition piece and a forward end cross sectional area is determined for the transition piece. The transition piece may be fabricated based on a constant slope of cross sectional area change between the aft end and the forward end.
摘要翻译： 本文公开了用于横截面积收敛减少和选择的装置，方法和系统。 在一个实施例中，对于过渡件确定后端横截面面积，并且为过渡件确定前端横截面面积。 可以基于后端和前端之间的横截面积变化的恒定斜率来制造过渡件。
-
-
-
-
-
-
-
-
-
搜索结果
32 条记录 (耗时 0.02 秒)
