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公开(公告)号：US20160215633A1
公开(公告)日：2016-07-28
申请号：US14916291
申请日：2014-09-03
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Christopher Drake , Christopher B. Lyons
CPC classification number: F01D9/041 , F01D5/187 , F01D9/065 , F01D11/005 , F01D25/12 , F01D25/246 , F05D2220/32 , F05D2240/35 , F23R3/04
Abstract: A gas turbine engine includes an engine static structure that has a fluid port. A turbine vane is supported relative to the engine static structure and includes a cooling passage. A flow splitter is provided between the engine static structure and the turbine vane. The flow splitter is configured to divide a flow upstream from the flow splitter into a first fluid flow provided to the fluid port and a second fluid flow provided to the cooling passage.
Abstract translation: 燃气涡轮发动机包括具有流体端口的发动机静态结构。 涡轮叶片相对于发动机静态结构被支撑并且包括冷却通道。 在发动机静态结构和涡轮叶片之间设置有分流器。 分流器构造成将流分配器上游的流分配成设置到流体端口的第一流体流和设置到冷却通道的第二流体流。
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公开(公告)号：US20160195275A1
公开(公告)日：2016-07-07
申请号：US14911158
申请日：2014-08-29
Applicant: United Technologies Corporation
Inventor： Christopher B. Lyons , Alexander W. Williams , Alexander Broulidakis
CPC classification number: F23R3/60 , F01D9/041 , F01D25/162 , F01D25/24 , F01D25/243 , F02C3/14 , F02C7/20 , F04D29/54 , F04D29/542 , F23R3/04 , Y02T50/671 , Y02T50/675
Abstract: A hybrid diffuser case for a gas turbine engine includes an outer diffuser case wall that extends downstream from an annular outer pre-diffuser case shroud. An inner diffuser case wall extends downstream from an annular inner pre-diffuser case shroud. A multiple of struts extend between the annular outer pre-diffuser case shroud and the annular inner pre-diffuser case shroud.
Abstract translation: 用于燃气涡轮发动机的混合式扩散器壳体包括从环形外部预扩散器壳体护罩的下游延伸的外部扩散器壳体壁。 内部扩散器壳壁从环形内部预扩散器壳体护罩的下游延伸。 多个支柱在环形外部预扩散器壳体护罩和环形内部预扩散器壳体护罩之间延伸。
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公开(公告)号：US09777634B2
公开(公告)日：2017-10-03
申请号：US14479566
申请日：2014-09-08
Applicant: United Technologies Corporation
Inventor： Christopher Drake , Christopher B. Lyons
Abstract: A tangential on-board injector assembly for a gas turbine engine includes an annular housing including a plenum. A plurality of discrete tubes is fluidly connected to the plenum and is configured to provide a cooling fluid to the annular housing.
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Patent Agency Ranking
公开(公告)号：US09745864B2
公开(公告)日：2017-08-29
申请号：US14665780
申请日：2015-03-23
Applicant: United Technologies Corporation
Inventor： Matthew R. Willett , Charles H. Warner , Gerald D. Cassella , Jonathan J. Earl , Christopher B. Lyons
CPC classification number: F01D25/246 , F01D9/041 , F05D2220/32 , F05D2230/10 , F05D2230/30 , F05D2230/60 , F05D2240/12 , F05D2240/14 , F05D2240/80
Abstract: Systems and methods are disclosed for anti-rotation lugs. A stator for a gas turbine engine may comprise an outer shroud, an inner shroud, and a plurality of vanes located between the outer shroud and the inner shroud. A plurality of anti-rotation lugs may be coupled to the inner shroud. The anti-rotation lugs may be configured to contact a diffuser case in order to prevent rotation of the stator. The anti-rotation lugs may comprise a body and a tapered shoulder. The tapered shoulder may distribute stress concentrations in the anti-rotation lugs.
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公开(公告)号：US20170059161A1
公开(公告)日：2017-03-02
申请号：US14836117
申请日：2015-08-26
Applicant: United Technologies Corporation
Inventor： Albert K. Cheung , Christos Adamopoulos , Christopher B. Lyons
CPC classification number: F23R3/16 , F02C6/06 , F02C6/08 , F02C7/12 , F02C7/18 , F02C9/18 , F05D2220/32 , F05D2240/35 , F05D2260/20 , F23C9/08 , F23C2900/09001 , F23R3/002 , F23R3/02 , F23R3/04 , F23R3/42 , F23R3/425 , F23R3/44 , F23R3/46 , F23R3/48 , F23R3/50 , F23R3/52 , F23R3/54 , F23R3/56 , F23R3/58
Abstract: An air extraction port at a combustor of a gas turbine engine includes a port inlet at a combustor case of the combustor having an inlet area, a port outlet having a final area, and a fluid passage extending from the port inlet to the port outlet to convey an airflow, the port inlet sized and configured to extract the airflow from the combustor case at the same nominal upstream Mach number with a tolerance of +/−0.05.
Abstract translation: 燃气涡轮发动机的燃烧器处的空气抽出口包括在燃烧器壳体处的具有入口区域的端口入口，具有最终区域的端口出口和从端口入口延伸到端口出口的流体通道 传送气流，端口入口的尺寸和构造可以在相同标称上游马赫数处从燃烧器壳体提取气流，其公差为+/- 0.05。
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公开(公告)号：US20160201915A1
公开(公告)日：2016-07-14
申请号：US14911205
申请日：2014-06-30
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Alexander W. Williams , Seth A. Max , Christopher B. Lyons
CPC classification number: F23R3/12 , F23R3/14 , F23R3/286 , F23R3/60 , F23R2900/00017 , Y02T50/675
Abstract: A swirler for a combustor of a gas turbine engine includes a swirler outer body with a male snap component and/or female snap component of a snap-fit interface defined around a swirler central longitudinal axis. A bulkhead assembly for a combustor of a gas turbine engine includes a swirler mounted to a bulkhead support shell through a snap-fit interface.
Abstract translation: 用于燃气涡轮发动机的燃烧器的旋流器包括旋流器外部主体，其具有围绕旋流器中心纵向轴线限定的卡扣配合接口的阳性卡扣部件和/或阴性卡扣部件。 用于燃气涡轮发动机的燃烧器的隔板组件包括通过卡扣配合接口安装到隔板支撑壳体上的旋流器。
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公开(公告)号：US20160177830A1
公开(公告)日：2016-06-23
申请号：US14910283
申请日：2014-08-01
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Vito Guardi , Christopher B. Lyons , Nathan Snape
CPC classification number: F02C7/18 , F01D5/18 , F01D9/065 , F01D25/14 , F02C3/04 , F02C6/08 , F02C7/185 , F02C9/18 , F05D2220/32 , F05D2240/35 , F05D2260/20 , F23R3/283 , F23R3/286 , Y02T50/676
Abstract: A turbine engine includes a compressor section, a combustor in fluid communication with the compressor section, and a turbine section in fluid communication with the combustor. Also included in the turbine engine is a mixing chamber. The mixing chamber is located between the compressor section and the combustor section and the mixing chamber is radially outward of a primary fluid flow path connecting the compressor section, the combustor section, and the turbine section.
Abstract translation: 涡轮发动机包括压缩机部分，与压缩机部分流体连通的燃烧器和与燃烧器流体连通的涡轮部分。 涡轮发动机中还包括混合室。 混合室位于压缩机部分和燃烧器部分之间，并且混合室在连接压缩机部分，燃烧器部分和涡轮部分的主流体流动路径的径向外侧。
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公开(公告)号：US20160090914A1
公开(公告)日：2016-03-31
申请号：US14890188
申请日：2013-05-10
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Christopher B. Lyons
CPC classification number: F02C7/18 , F01D5/02 , F01D9/02 , F01D9/065 , F01D25/08 , F01D25/12 , F01D25/162 , F01D25/24 , F02C3/06 , F02C7/04 , F02C7/12 , F02C7/185 , F05D2210/12 , F05D2220/32 , F05D2220/3219 , F05D2240/12 , F05D2240/35 , F05D2260/211 , F05D2260/213 , Y02T50/676
Abstract: An inner diffuser case for a turbine engine includes a fore gas path edge and an aft gas path edge defining a strut, wherein each of the fore gas path edge and the aft gas path edge include a gas path opening, a support cone structure extending radially outward from the strut, wherein the support cone structure is operable to structurally connect the strut to a turbine engine case, a diffuser case skirt structure extending radially inward from the strut, wherein the diffuser case skirt structure is operable to structurally connect the diffuser case strut to an inner support structure of the turbine engine, and at least one direct feed air passage passing radially through the strut including a radially outward upper mixing chamber opening and a radially inward direct air feed opening, the direct air feed opening is connected to a direct air feed.
Abstract translation: 用于涡轮发动机的内部扩散器壳体包括限定支柱的前部气体路径边缘和后部气体路径边缘，其中前部气体路径边缘和后部气体路径边缘中的每一个包括气体通道开口，径向延伸的支撑锥形结构 从支柱向外，其中支撑锥形结构可操作以将支柱结构地连接到涡轮发动机壳体，从支柱径向向内延伸的扩散器壳体裙部结构，其中扩散器壳体裙部结构可操作以在结构上连接扩散器壳体支柱 到达涡轮发动机的内部支撑结构，以及至少一个直接通过支柱的直接进料空气通道，其包括径向向外的上部混合室开口和径向向内的直接空气供给开口，直接空气供给开口连接到直接 空气饲料
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