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1. 发明授权

US08973371B2 Gas turbine engine with turbine cooling arrangement 有权
标题翻译：带涡轮冷却装置的燃气轮机
公开(公告)号：US08973371B2
公开(公告)日：2015-03-10
申请号：US13224894
申请日：2011-09-02
申请人： Jonathan M King , Crispin D. Bolgar , Guy D. Snowsill , Michael J. Sheath , Geoffrey M Dailey
发明人： Jonathan M King , Crispin D. Bolgar , Guy D. Snowsill , Michael J. Sheath , Geoffrey M Dailey
IPC分类号： F02C6/08 , F02C3/13 , F02C7/18 , F01D5/08 , F01D11/00 , F01D11/04 , F01D11/06
CPC分类号： F02C6/08 , F01D5/081 , F01D5/082 , F01D11/001 , F01D11/04 , F01D11/06 , F02C3/13 , F02C7/18
摘要： A gas turbine engine comprising a turbine section cooling system and a method of cooling a turbine section of a gas turbine engine is provided. The gas turbine engine comprises in flow series a compressor section, a combustor, and a turbine section, the engine further comprising a turbine section cooling system. The turbine section cooling system including a first compressed air bleed arrangement and a second compressed air bleed arrangement. The first compressed air bleed arrangement bleeds a first flow of compressed air from a high pressure stage of the compressor section. The first flow of compressed air bypasses the combustor and arrives at the turbine section to form a sealing and/or cooling flow at a row of stator vanes upstream of an adjacent rotor disc. The second compressed air bleed arrangement bleeds a second flow of compressed air from one or more lower pressure stages of the compressor section. The second flow of compressed air bypasses the combustor and arrives at the turbine section to form a cooling flow. A first portion of the cooling flow is routed to a front face of the rotor disc and a second portion of the cooling flow is routed to a rear face of the rotor disc.
摘要翻译：提供一种燃气涡轮发动机，其包括涡轮部分冷却系统和冷却燃气涡轮发动机的涡轮部分的方法。燃气涡轮发动机包括流动系列，压缩机部分，燃烧器和涡轮部分，发动机还包括涡轮部分冷却系统。涡轮部分冷却系统包括第一压缩空气排放装置和第二压缩空气排放装置。第一压缩排气装置从压缩机部分的高压级排出第一流的压缩空气。压缩空气的第一流动绕过燃烧器并到达涡轮部分，以在相邻转子盘的上游的一排定子叶片上形成密封和/或冷却流。第二压缩空气排出装置从压缩机部分的一个或多个较低压力级渗出第二压缩空气流。压缩空气的第二流动绕过燃烧器并到达涡轮部分以形成冷却流。冷却流的第一部分被引导到转子盘的前表面，并且冷却流的第二部分被引导到转子盘的后表面。

2. 发明授权

US07874799B2 Flow cavity arrangement 有权
标题翻译：流腔布置
公开(公告)号：US07874799B2
公开(公告)日：2011-01-25
申请号：US11905463
申请日：2007-10-01
申请人： Colin Young , Guy D. Snowsill
发明人： Colin Young , Guy D. Snowsill
IPC分类号： F01D5/08 , F01D5/18
CPC分类号： F01D5/082 , F01D11/04
摘要： It is known with regard to particularly cavities below high pressure turbine discs that mixing of hot gas leakage flows through an inner seal with cooling flows can diminish the effectiveness of that cooling flow when presented to other parts for cooling. By providing a path within a wall which is particularly shaped in portions it is possible to provide entrainment of a hot leakage gas flow away from entry into the cavity. Thus, the cooling flow retains a higher cooling effect and maintains its swirling nature in comparison with prior arrangements where mixing with the hot leakage flow occurred.
摘要翻译：关于高压涡轮机盘下面的特别是空腔是已知的，热气体泄漏的混合通过内部密封件与冷却流动的混合可以降低当冷却流体被提供给其它部件用于冷却时的有效性。通过在壁内提供特别成形的路径，可以使热泄漏气流的夹带远离进入空腔。因此，与先前的布置相比，冷却流保持更高的冷却效果并保持其旋转性质，其中发生与热泄漏流的混合。

3. 发明申请

US20080310950A1 Flow cavity arrangement 有权
标题翻译：流腔布置
公开(公告)号：US20080310950A1
公开(公告)日：2008-12-18
申请号：US11905463
申请日：2007-10-01
申请人： Colin Young , Guy D. Snowsill
发明人： Colin Young , Guy D. Snowsill
IPC分类号： F02C7/12 , F01D11/02
CPC分类号： F01D5/082 , F01D11/04
摘要： It is known with regard to particularly cavities below high pressure turbine discs that mixing of hot gas leakage flows through an inner seal with cooling flows can diminish the effectiveness of that cooling flow when presented to other parts for cooling. By providing a path within a wall which is particularly shaped in portions it is possible to provide entrainment of a hot leakage gas flow away from entry into the cavity. Thus, the cooling flow retains a higher cooling effect and maintains its swirling nature in comparison with prior arrangements where mixing with the hot leakage flow occurred.
摘要翻译：关于高压涡轮机盘下面的特别是空腔是已知的，热气体泄漏的混合通过内部密封件与冷却流动的混合可以降低当冷却流体被提供给其它部件用于冷却时的有效性。通过在壁内提供特别成形的路径，可以使热泄漏气流的夹带远离进入空腔。因此，与先前的布置相比，冷却流保持更高的冷却效果并保持其旋转性质，其中发生与热泄漏流的混合。

4. 发明申请

US20070189890A1 Gas turbine engine rotor ventilation arrangement 有权
标题翻译：燃气轮机发动机转子通风装置
公开(公告)号：US20070189890A1
公开(公告)日：2007-08-16
申请号：US11702589
申请日：2007-02-06
申请人： Guy D. Snowsill , Timothy J. Scanlon , Colin Young , Leo V. Lewis
发明人： Guy D. Snowsill , Timothy J. Scanlon , Colin Young , Leo V. Lewis
IPC分类号： F03B11/00
CPC分类号： F01D5/082 , F01D5/085 , F05D2260/20 , F05D2270/112
摘要： A rotor assembly for a gas turbine engine, the rotor assembly comprises at least two rotors defining a cavity therebetween. A first rotor defines a cooling air inlet in its radially inward portion. A second rotor defines a cooling air outlet in its radially outward portion, such that the cooling air passes radially outwardly through the cavity.
摘要翻译：一种用于燃气涡轮发动机的转子组件，转子组件包括至少两个在其间限定空腔的转子。第一转子在其径向向内部分限定冷却空气入口。第二转子在其径向向外的部分中限定冷却空气出口，使得冷却空气径向向外通过空腔。

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