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公开(公告)号：US08534076B2
公开(公告)日：2013-09-17
申请号：US12481441
申请日：2009-06-09
CPC分类号： F01D9/023
摘要： A combustor-turbine seal interface is provided for deployment within a gas turbine engine. In one embodiment, the combustor-turbine assembly a combustor, a turbine nozzle downstream of the combustor, and a first compliant dual seal assembly. The first compliant dual seal assembly includes a compliant seal wall sealingly coupled between the combustor and the turbine nozzle, a first compression seal sealingly disposed between the compliant seal wall and the turbine nozzle, and a first bearing seal generally defined by the compliant seal wall and the turbine nozzle. The first bearing seal is sealingly disposed in series with the first compression seal.
摘要翻译： 提供燃烧器 - 涡轮机密封接口用于部署在燃气涡轮发动机内。 在一个实施例中，燃烧器 - 涡轮机组件，燃烧器，燃烧器下游的涡轮喷嘴和第一柔性双重密封组件。 第一柔性双密封组件包括密封地联接在燃烧器和涡轮喷嘴之间的顺应性密封壁，密封地设置在柔性密封壁和涡轮喷嘴之间的第一压缩密封件，以及通常由柔性密封壁和 涡轮喷嘴。 第一轴承密封件与第一压缩密封件密封地设置成串联。
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公开(公告)号：US20100307166A1
公开(公告)日：2010-12-09
申请号：US12481441
申请日：2009-06-09
CPC分类号： F01D9/023
摘要： A combustor-turbine seal interface is provided for deployment within a gas turbine engine. In one embodiment, the combustor-turbine assembly a combustor, a turbine nozzle downstream of the combustor, and a first compliant dual seal assembly. The first compliant dual seal assembly includes a compliant seal wall sealingly coupled between the combustor and the turbine nozzle, a first compression seal sealingly disposed between the compliant seal wall and the turbine nozzle, and a first bearing seal generally defined by the compliant seal wall and the turbine nozzle. The first bearing seal is sealingly disposed in series with the first compression seal.
摘要翻译： 提供燃烧器 - 涡轮机密封接口用于部署在燃气涡轮发动机内。 在一个实施例中，燃烧器 - 涡轮机组件，燃烧器，燃烧器下游的涡轮喷嘴和第一柔性双重密封组件。 第一柔性双密封组件包括密封地联接在燃烧器和涡轮喷嘴之间的顺应性密封壁，密封地设置在柔性密封壁和涡轮喷嘴之间的第一压缩密封件，以及通常由柔性密封壁和 涡轮喷嘴。 第一轴承密封件与第一压缩密封件密封地设置成串联。
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3.发明授权Turbine nozzle assembly including radially-compliant spring member for gas turbine engine 有权涡轮喷嘴组件，包括用于燃气涡轮发动机的径向柔性弹簧构件公开(公告)号：US08388307B2
公开(公告)日：2013-03-05
申请号：US12506904
申请日：2009-07-21
IPC分类号： F01D25/24
CPC分类号： F01D9/02 , F01D9/042 , F05D2260/38 , F05D2260/941
摘要： Embodiments of a turbine nozzle assembly are provided for deployment within a gas turbine engine (GTE) including a first GTE-nozzle mounting interface. In one embodiment, the turbine nozzle assembly includes a turbine nozzle flowbody, a first mounting flange configured to be mounted to the first GTE-nozzle mounting interface, and a first radially-compliant spring member coupled between the turbine nozzle flowbody and the first mounting flange. The turbine nozzle flowbody has an inner nozzle endwall and an outer nozzle endwall, which is fixedly coupled to the inner nozzle endwall and which cooperates therewith to define a flow passage through the turbine nozzle flowbody. The first radially-compliant spring member accommodates relative thermal movement between the turbine nozzle flowbody and the first mounting flange to alleviate thermomechanical stress during operation of the GTE.
摘要翻译： 涡轮喷嘴组件的实施例被提供用于部署在包括第一GTE喷嘴安装界面的燃气涡轮发动机（GTE）内。 在一个实施例中，涡轮喷嘴组件包括涡轮喷嘴流动体，构造成安装到第一GTE喷嘴安装界面的第一安装凸缘以及联接在涡轮喷嘴流体和第一安装凸缘之间的第一径向顺应弹簧构件 。 涡轮喷嘴流动体具有内部喷嘴端壁和外部喷嘴端壁，其固定地联接到内部喷嘴端壁并与其配合以限定通过涡轮喷嘴流体的流动通道。 第一径向顺应弹簧构件适应涡轮喷嘴流体和第一安装凸缘之间的相对热运动，以减轻GTE操作期间的热机械应力。
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4.发明申请TURBINE NOZZLE ASSEMBLY INCLUDING RADIALLY-COMPLIANT SPRING MEMBER FOR GAS TURBINE ENGINE 有权涡轮喷嘴组件，包括用于气体涡轮发动机的放射性弹簧组件公开(公告)号：US20110020118A1
公开(公告)日：2011-01-27
申请号：US12506904
申请日：2009-07-21
IPC分类号： F01D9/04
CPC分类号： F01D9/02 , F01D9/042 , F05D2260/38 , F05D2260/941
摘要： Embodiments of a turbine nozzle assembly are provided for deployment within a gas turbine engine (GTE) including a first GTE-nozzle mounting interface. In one embodiment, the turbine nozzle assembly includes a turbine nozzle flowbody, a first mounting flange configured to be mounted to the first GTE-nozzle mounting interface, and a first radially-compliant spring member coupled between the turbine nozzle flowbody and the first mounting flange. The turbine nozzle flowbody has an inner nozzle endwall and an outer nozzle endwall, which is fixedly coupled to the inner nozzle endwall and which cooperates therewith to define a flow passage through the turbine nozzle flowbody. The first radially-compliant spring member accommodates relative thermal movement between the turbine nozzle flowbody and the first mounting flange to alleviate thermomechanical stress during operation of the GTE.
摘要翻译： 涡轮喷嘴组件的实施例被提供用于部署在包括第一GTE喷嘴安装界面的燃气涡轮发动机（GTE）内。 在一个实施例中，涡轮喷嘴组件包括涡轮喷嘴流动体，构造成安装到第一GTE喷嘴安装界面的第一安装凸缘以及联接在涡轮喷嘴流体和第一安装凸缘之间的第一径向顺应弹簧构件 。 涡轮喷嘴流动体具有内部喷嘴端壁和外部喷嘴端壁，其固定地联接到内部喷嘴端壁并与其配合以限定通过涡轮喷嘴流动体的流动通道。 第一径向顺应弹簧构件适应涡轮喷嘴流体和第一安装凸缘之间的相对热运动，以减轻GTE操作期间的热机械应力。
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公开(公告)号：US07007480B2
公开(公告)日：2006-03-07
申请号：US10410791
申请日：2003-04-09
申请人： Ly D. Nguyen , Gregory O. Woodcock , Stony Kujala
发明人： Ly D. Nguyen , Gregory O. Woodcock , Stony Kujala
CPC分类号： F23R3/283 , F23R3/60 , F23R2900/00014 , F23R2900/00017
摘要： A multi-axial pivoting liner within the combustion system of a turbine engine allows the system to work with minimum thermal interference, especially during system operation at transient conditions, by allowing the liner to pivot and slide about its centerline and relative to the turbine scroll. The pivoting liner has the ability to control and minimize air leakage from part to part, for example, from the liner to the turbine scroll and liner to the surrounding structures, during various operating conditions. Additionally, the liner provides for easy assembly with no flow path steps. Finally, the pivoting liner tolerates thermal and mechanical stresses and minimizes thermal wear.
摘要翻译： 在涡轮发动机的燃烧系统内的多轴旋转衬套允许系统以最小的热干扰工作，特别是在瞬态条件下的系统运行期间，通过允许衬套围绕其中心线枢转并且相对于涡轮机涡卷滑动。 在各种操作条件下，枢转衬套具有控制和最小化从一部分到另一部分的空气泄漏的能力，例如从衬套到涡轮机涡旋件和衬套到周围结构。 另外，衬套提供了容易组装，没有流动路径的步骤。 最后，旋转衬垫可承受热和机械应力，并最大限度地减少热磨损。
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6.发明授权Forming and assembly method for multi-axial pivoting combustor liner in gas turbine engine 失效燃气轮机发动机多轴转动燃烧器衬管的成形和组装方法公开(公告)号：US06912782B2
公开(公告)日：2005-07-05
申请号：US10410794
申请日：2003-04-09
申请人： Ly D. Nguyen , Gregory O. Woodcock , Stony Kujala
发明人： Ly D. Nguyen , Gregory O. Woodcock , Stony Kujala
CPC分类号： F23R3/002 , F23R3/60 , F23R2900/00017 , Y10T29/49231 , Y10T29/49316 , Y10T29/4932
摘要： A multi-axial pivoting liner within the combustion system of a turbine engine allows the system to work with minimum thermal interference, especially during system operation at transient conditions, by allowing the liner to pivot and slide about its centerline and relative to the turbine scroll. The pivoting liner has the ability to control and minimize air leakage from part to part, for example, from the liner to the turbine scroll, during various operating conditions. Additionally, the liner provides for easy assembly with no flow path steps. Finally, the pivoting liner tolerates thermal and mechanical stresses and minimizes thermal wear.
摘要翻译： 在涡轮发动机的燃烧系统内的多轴旋转衬套允许系统以最小的热干扰工作，特别是在瞬态条件下的系统运行期间，通过允许衬套围绕其中心线枢转并且相对于涡轮机涡卷滑动。 在各种操作条件下，枢转衬套具有控制和最小化从一部分到另一部分的空气泄漏的能力，例如从衬套到涡轮涡旋。 另外，衬套提供了容易组装，没有流动路径的步骤。 最后，旋转衬垫可承受热和机械应力，并最大限度地减少热磨损。
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7.发明授权Multi-action on multi-surface seal with turbine scroll retention method in gas turbine engine 失效多功能多功能涡轮发动机涡轮涡轮保持法多表面密封公开(公告)号：US07093448B2
公开(公告)日：2006-08-22
申请号：US10682217
申请日：2003-10-08
申请人： Ly D. Nguyen , Gregory O. Woodcock , Stony Kujala
发明人： Ly D. Nguyen , Gregory O. Woodcock , Stony Kujala
摘要： A gas turbine engine comprises a turbine scroll inside a combustor housing, discouragers with 90-degree bending angles, a radial nozzle contacting a forward bayonet on the forward side of the turbine scroll at a bayonet engagement point and a B-width measured between the discouragers. Retaining ring maintains the size of the B-width. The turbine scroll may have eight surfaces sealing at four locations and a provision to maintain constant “B-width” for the thin sheet metal scroll within the combustion system. The design allows the scroll to operate at high temperature while maintaining lowest possible thermal and mechanical stresses. It can be easily assembled with excellent capability to control gas leakage and minimal component interface wearing or fretting. The gas turbine engine is adapted for aircraft, spacecraft, missiles, and other flight vehicles, especially high performance, high cycle flight vehicles.
摘要翻译： 燃气涡轮发动机包括在燃烧器壳体内的涡轮机涡旋件，具有90度弯曲角度的气门，在卡口接合点处与涡轮机涡旋体的前侧接触前方卡口的径向喷嘴和在气门机构之间测量的B宽度 。 保持环保持B宽度的大小。 涡轮机涡旋件可以在四个位置处具有八个表面密封，并且在燃烧系统内为薄板金属涡卷保持恒定的“B宽度”。 该设计允许滚动体在高温下运行，同时保持尽可能低的热和机械应力。 它可以很容易地组装，具有极好的控制气体泄漏的能力和最小的组件界面磨损或微动。 燃气涡轮发动机适用于飞机，航天器，导弹和其他飞行器，特别是高性能，高周期的飞行器。
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公开(公告)号：US06962480B2
公开(公告)日：2005-11-08
申请号：US10712434
申请日：2003-11-12
CPC分类号： F01D9/026 , F01D9/045 , F05D2230/642
摘要： A turbine scroll retention ring may comprise a retainer ring, a plurality of ring fingers, and a plurality of ring joggles. The turbine scroll retention ring may surround and be attached to a radial nozzle. The ring joggles may allow for thermal growth variations between the radial nozzle and the turbine scroll retention ring. The radially outer end portions of the ring fingers may be in contact with a turbine scroll component (for example, an aft scroll ring), such that the turbine scroll retention ring may force contact between the turbine scroll component and the radial nozzle. The finger joggles of the ring fingers may allow for thermal growth variations between the radial nozzle and the turbine scroll component. The turbine scroll retention ring may provide constant axial loading to the aft scroll ring during all engine operating conditions.
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公开(公告)号：US20050241316A1
公开(公告)日：2005-11-03
申请号：US10835169
申请日：2004-04-28
申请人： Ly Nguyen , Stony Kujala , David Walhood , Ian Critchley , Gregory Woodcock , Jurgen Schumacher
发明人： Ly Nguyen , Stony Kujala , David Walhood , Ian Critchley , Gregory Woodcock , Jurgen Schumacher
CPC分类号： F23R3/10 , F23R2900/03041 , Y02T50/675
摘要： A dome for a combustion chamber may have a plurality of effusion holes therein to provide efficient cooling while preventing carbon formation on the dome and chamber walls of the combustion chamber. Conventional dome cooling designs, using dome louvers, for example, may become corroded and/or may allow for ingestion of carbon particles that may build up and eventually separate from the dome. Furthermore, the dome cooling design of the present invention allows for the use of a lower profile dome as compared with conventional domes, thereby maximizing liner volume in the constrained combustion envelope while reducing combustor case weight. Additionally, the dome effusion cooling design of the present invention requires the use of less thermal barrier coating, as compared to conventional designs, in order to minimize thermal variation within the dome and between the dome and the combustor wall. A method for uniformly cooling a dome of a combustion chamber of an engine is also disclosed.
摘要翻译： 用于燃烧室的圆顶可以在其中具有多个渗出孔以提供有效的冷却，同时防止燃烧室的圆顶和室壁上的碳形成。 例如，使用圆顶百叶窗的常规圆顶冷却设计可能被腐蚀和/或可能允许摄取可能积聚并最终与圆顶分离的碳颗粒。 此外，本发明的圆顶冷却设计允许与常规圆顶相比使用下部轮廓圆顶，由此在减小燃烧器壳体重量的同时最大化受限燃烧包层中的衬管体积。 此外，与传统设计相比，本发明的圆顶渗出冷却设计需要使用较少的热障涂层，以便最小化圆顶内部和圆顶与燃烧室壁之间的热变化。 还公开了一种用于均匀冷却发动机的燃烧室的圆顶的方法。
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10.发明申请公开(公告)号：US20050188698A1
公开(公告)日：2005-09-01
申请号：US10386771
申请日：2003-03-11
申请人： Ly Nguyen , Hakan Aksoy , Stony Kujala , Cristoper Frost
发明人： Ly Nguyen , Hakan Aksoy , Stony Kujala , Cristoper Frost
摘要： A conical helical design for a turbine combustor scroll utilizes as much cavity of the combustor housing as possible by adding an axial shift and an irregular cross sectional shape in the scroll without adversely effecting aerodynamic performance. The axial shift region of the combustor scroll extends the cross-sectional area centroid of the scroll beyond the scroll's discharge area B-width. The resulting scroll design allows for the use of a high performance engine with a larger combustor while reducing the weight of the system by making the combustor housing as small as possible. Furthermore, the scroll design increases the air velocity for convection cooling by reducing the gap between the scroll and the housing. The turbine scroll of the present invention is useful in engines for which high performance is required, such as certain high performance aircraft.
摘要翻译： 用于涡轮机燃烧器涡旋盘的锥形螺旋设计通过在涡旋中增加轴向移动和不规则横截面形状而尽可能多地利用燃烧器壳体的空腔，而不会不利地影响空气动力性能。 燃烧器涡旋件的轴向移动区域将涡旋件的横截面积重心延伸超过涡旋件的排放区域B-宽度。 所得到的涡卷设计允许使用具有较大燃烧器的高性能发动机，同时通过使燃烧器壳体尽可能小地减小系统的重量。 此外，涡旋设计通过减小涡旋件和壳体之间的间隙来增加用于对流冷却的空气速度。 本发明的涡轮涡旋盘可用于需要高性能的发动机，例如某些高性能飞机。
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