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1. 发明授权

US07717669B2 Load absorption arrangements for gas turbine engines 有权
标题翻译：燃气轮机的负载吸收装置
公开(公告)号：US07717669B2
公开(公告)日：2010-05-18
申请号：US11104576
申请日：2005-04-13
申请人： Michael J. Sheath , Paul S. McCabe
发明人： Michael J. Sheath , Paul S. McCabe
IPC分类号： F01D17/16
CPC分类号： F01D17/162 , F01D25/04
摘要： A load absorption arrangement 40 for absorbing loads in a variable stator vane positioning system of a gas turbine engine includes a valve 42 which has a first operating condition to enable the load absorption arrangement 40 to transmit load, and a second operating condition, which is operable above a predetermined load, in which the valve 42 can release to enable the load absorption arrangement 40 to absorb the load thereon. The arrangement 40 is particularly suitable for absorbing shock loads which may arise under engine surge.
摘要翻译：用于吸收燃气涡轮发动机的可变定子叶片定位系统中的载荷的负载吸收装置40包括阀42，阀42具有使负载吸收装置40能够传递负载的第一操作条件和可操作的第二操作条件高于预定负载，其中阀42可以释放以使负载吸收装置40能够吸收其上的负载。装置40特别适用于吸收在发动机喘振时可能产生的冲击载荷。

2. 发明申请

US20090318238A1 Multi-rotational crankshaft arrangement 有权
标题翻译：多转曲轴装置
公开(公告)号：US20090318238A1
公开(公告)日：2009-12-24
申请号：US12453775
申请日：2009-05-21
申请人： Crispin D. Bolgar , Michael J. Sheath
发明人： Crispin D. Bolgar , Michael J. Sheath
IPC分类号： F16D7/04
CPC分类号： F02C9/20 , F01D17/162 , F04D29/563 , F16C3/10 , F16C3/22 , F16C2360/23
摘要： A control mechanism for moving at least two components of a gas turbine engine, the control mechanism comprises first and second crankshafts and a torsion bar connected to both crankshafts, each crankshaft is connected to a different component, the crankshafts engage one another via one-way abutment means and the torsion bar is pre-twisted so that up to a predetermined rotational extent the two crankshafts rotate together and beyond that extent only the first crankshaft rotates, thereby one of the two components moves more than the other component.
摘要翻译：用于移动燃气涡轮发动机的至少两个部件的控制机构，所述控制机构包括第一和第二曲轴以及连接到两个曲轴的扭杆，每个曲轴连接到不同的部件，所述曲轴通过单向连接邻接装置和扭杆被预扭转，使得两个曲轴一起旋转并且超过该范围直到预定旋转范围仅仅第一曲轴旋转，从而两个部件中的一个移动比另一个部件移动。

3. 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。

4. 发明申请

US20120060507A1 GAS TURBINE ENGINE 有权
标题翻译：气体涡轮发动机
公开(公告)号：US20120060507A1
公开(公告)日：2012-03-15
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： F02C7/18 , F02C3/04
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 fowl 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处形成密封和/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产生冷却流。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。

5. 发明授权

US08052373B2 Multi-rotational crankshaft arrangement 有权
标题翻译：多转曲轴装置
公开(公告)号：US08052373B2
公开(公告)日：2011-11-08
申请号：US12453775
申请日：2009-05-21
申请人： Crispin D. Bolgar , Michael J. Sheath
发明人： Crispin D. Bolgar , Michael J. Sheath
IPC分类号： F01D19/00 , F01D17/06 , F01D21/02 , F03D7/00 , F01B25/06 , F03B15/06 , F04D15/00 , F04D27/00
CPC分类号： F02C9/20 , F01D17/162 , F04D29/563 , F16C3/10 , F16C3/22 , F16C2360/23
摘要： A control mechanism for moving at least two components of a gas turbine engine, the control mechanism comprises first and second crankshafts and a torsion bar connected to both crankshafts, each crankshaft is connected to a different component, the crankshafts engage one another via one-way abutment means and the torsion bar is pre-twisted so that up to a predetermined rotational extent the two crankshafts rotate together and beyond that extent only the first crankshaft rotates, thereby one of the two components moves more than the other component.
摘要翻译：用于移动燃气涡轮发动机的至少两个部件的控制机构，所述控制机构包括第一和第二曲轴以及连接到两个曲轴的扭杆，每个曲轴连接到不同的部件，所述曲轴通过单向连接邻接装置和扭杆被预扭转，使得两个曲轴一起旋转并且超过该范围直到预定旋转范围仅仅第一曲轴旋转，从而两个部件中的一个移动比另一个部件移动。

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