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1. 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。

2. 发明授权

US08864406B2 Splined couplings 有权
标题翻译：花键联轴器
公开(公告)号：US08864406B2
公开(公告)日：2014-10-21
申请号：US12588116
申请日：2009-10-05
申请人： Crispin D Bolgar
发明人： Crispin D Bolgar
IPC分类号： F16D1/00 , F16D1/108 , F16D1/10
CPC分类号： F16D1/108 , F01D5/06 , F16D2001/103 , Y10T29/4932 , Y10T403/559 , Y10T403/7026 , Y10T403/7035
摘要： Apparatus is provided comprising first and second coaxial shafts, the first and second shafts extending along, and being rotatable about, a central axis. The first and second shafts are coupled together by a splined major coupling at a coupling region of the apparatus, which major coupling enables the shafts to co-rotate about the central axis. A torque element is connected to the first and second shafts, the torque element being operable to force the first and second shafts to relatively rotate about the central axis in order to apply a preload to the major coupling. The apparatus may be comprised in a gas turbine engine, whereupon the first shaft may be a fan shaft and the second shaft may be a LP turbine shaft.
摘要翻译：提供了包括第一和第二同轴轴的设备，第一和第二轴沿着中心轴线延伸并且可围绕中心轴线旋转。第一和第二轴通过在装置的联接区域处的花键主联接件联接在一起，该主联接使得轴能够围绕中心轴线共旋转。扭矩元件连接到第一和第二轴，扭矩元件可操作以迫使第一和第二轴围绕中心轴线相对旋转，以便将主负载施加到主联轴器。该装置可以包括在燃气涡轮发动机中，于是第一轴可以是风扇轴，而第二轴可以是LP涡轮轴。

3. 发明授权

US08727709B2 Casing component 有权
标题翻译：套管部件
公开(公告)号：US08727709B2
公开(公告)日：2014-05-20
申请号：US12862102
申请日：2010-08-24
申请人： Crispin D. Bolgar
发明人： Crispin D. Bolgar
IPC分类号： F01D25/26
CPC分类号： F01D11/22
摘要： A casing component (2) of a turbomachine, the casing component (2) comprising: a plurality of casing elements (14) which define a diameter of the casing component; and an actuation means operable to change the diameter of the casing component (2), wherein the actuation means changes the diameter of the casing component (2) as a function of a rotational speed of a rotatable component (4) disposed within the casing component (2).
摘要翻译：一种涡轮机的壳体部件（2），所述壳体部件（2）包括：限定所述壳体部件的直径的多个壳体元件（14）; 以及可操作以改变所述壳体部件（2）的直径的致动装置，其中所述致动装置根据设置在所述壳体部件（2）内的可旋转部件（4）的旋转速度来改变所述壳体部件（2）的直径，（2）。

4. 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。

5. 发明授权

US08677733B2 Ducted fan gas turbine assembly 有权
标题翻译：风机燃气轮机总成
公开(公告)号：US08677733B2
公开(公告)日：2014-03-25
申请号：US13549738
申请日：2012-07-16
申请人： Peter K. Beardsley , Crispin D. Bolgar
发明人： Peter K. Beardsley , Crispin D. Bolgar
IPC分类号： F02K3/02
CPC分类号： F02K1/72 , F02K1/09 , F02K3/075 , Y02T50/671
摘要： A ducted fan gas turbine assembly has a propulsive fan driven by a core engine. The turbine assembly has an annular bypass duct which receives an airflow from the fan and is bounded on the radially inward side by the core engine and on the radially outward side by an engine nacelle. The turbine assembly has a thrust reverser assembly having a vane arrangement including a first set of turning vanes for channelling airflow from the duct in a rearward direction, a second set of turning vanes for channelling airflow from the bypass duct in a forward direction. The thrust reverser assembly includes a plurality of blocker doors which are deployable to block the bypass duct. The nacelle has stationary and movable cowl portions that cooperate with the thrust reverser assembly to provide several operational configurations.
摘要翻译：管式风扇燃气轮机组件具有由核心发动机驱动的推进风扇。涡轮组件具有环形旁通管道，其接收来自风扇的气流并且通过核心发动机在径向向内侧并且在径向向外侧由发动机机舱限定。涡轮机组件具有推力反向器组件，该推力反向器组件具有叶片装置，该叶片装置包括第一组转动叶片，用于在向后方向上引导来自管道的气流;第二组转动叶片，用于在向前方向上引导来自旁路管道的气流。推力反向器组件包括可展开以阻挡旁路管道的多个阻挡门。机舱具有与推力反向器组件配合以提供若干操作构造的固定和可移动的外罩部分。

6. 发明申请

US20130025259A1 DUCTED FAN GAS TURBINE ASSEMBLY 有权
标题翻译：导风扇瓦斯组件
公开(公告)号：US20130025259A1
公开(公告)日：2013-01-31
申请号：US13549738
申请日：2012-07-16
申请人： Peter K. BEARDSLEY , Crispin D. BOLGAR
发明人： Peter K. BEARDSLEY , Crispin D. BOLGAR
IPC分类号： F02K1/68
CPC分类号： F02K1/72 , F02K1/09 , F02K3/075 , Y02T50/671
摘要： A ducted fan gas turbine assembly has a propulsive fan driven by a core engine. The turbine assembly has an annular bypass duct which receives an airflow from the fan and is bounded on the radially inward side by the core engine and on the radially outward side by an engine nacelle. The turbine assembly has a thrust reverser assembly having a vane arrangement including a first set of turning vanes for channelling airflow from the duct in a rearward direction, a second set of turning vanes for channelling airflow from the bypass duct in a forward direction. The thrust reverser assembly includes a plurality of blocker doors which are deployable to block the bypass duct. The nacelle has stationary and movable cowl portions that cooperate with the thrust reverser assembly to provide several operational configurations.
摘要翻译：管式风扇燃气轮机组件具有由核心发动机驱动的推进风扇。涡轮组件具有环形旁通管道，其接收来自风扇的气流并且通过核心发动机在径向向内侧并且在径向向外侧由发动机机舱限定。涡轮机组件具有推力反向器组件，该推力反向器组件具有叶片装置，该叶片装置包括第一组转动叶片，用于在向后方向上引导来自管道的气流;第二组转动叶片，用于在向前方向上引导来自旁路管道的气流。推力反向器组件包括可展开以阻挡旁路管道的多个阻挡门。机舱具有与推力反向器组件协作以提供若干操作构造的固定和可移动的外罩部分。

7. 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。

8. 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。

9. 发明申请

US20100087263A1 Splined couplings 有权
标题翻译：花键联轴器
公开(公告)号：US20100087263A1
公开(公告)日：2010-04-08
申请号：US12588116
申请日：2009-10-05
申请人： Crispin D. BOLGAR
发明人： Crispin D. BOLGAR
IPC分类号： F16D3/18 , B21K25/00
CPC分类号： F16D1/108 , F01D5/06 , F16D2001/103 , Y10T29/4932 , Y10T403/559 , Y10T403/7026 , Y10T403/7035
摘要： Apparatus is provided comprising first and second coaxial shafts, the first and second shafts extending along, and being rotatable about, a central axis. The first and second shafts are coupled together by a splined major coupling at a coupling region of the apparatus, which major coupling enables the shafts to co-rotate about the central axis. A torque element is connected to the first and second shafts, the torque element being operable to force the first and second shafts to relatively rotate about the central axis in order to apply a preload to the major coupling. The apparatus may be comprised in a gas turbine engine, whereupon the first shaft may be a fan shaft and the second shaft may be a LP turbine shaft.
摘要翻译：提供了包括第一和第二同轴轴的设备，第一和第二轴沿着中心轴线延伸并且可围绕中心轴线旋转。第一和第二轴通过在装置的联接区域处的花键主联接件联接在一起，该主联接使得轴能够围绕中心轴线共旋转。扭矩元件连接到第一和第二轴，扭矩元件可操作以迫使第一和第二轴围绕中心轴线相对旋转，以便将主负载施加到主联轴器。该装置可以包括在燃气涡轮发动机中，于是第一轴可以是风扇轴，而第二轴可以是LP涡轮轴。

10. 发明授权

US09103281B2 Gas turbine engine havinga rotatable off-take passage in a compressor section 有权
标题翻译：燃气涡轮发动机在压缩机部分具有可旋转的脱离通道
公开(公告)号：US09103281B2
公开(公告)日：2015-08-11
申请号：US13216691
申请日：2011-08-24
申请人： Jonathan M King , Crispin D Bolgar , Guy D Snowsill
发明人： Jonathan M King , Crispin D Bolgar , Guy D Snowsill
IPC分类号： F02C6/08 , F01D9/06 , F04D27/02 , F01D5/08 , F02C9/20
CPC分类号： F02C6/08 , D01H2700/22 , F01D5/081 , F01D9/065 , F02C9/20 , F04D27/023 , F04D29/321
摘要： A gas turbine engine has a compressor section with rotational compressor components rotatable with respect to static compressor components. A compressed air bleed arrangement is provided to cool one or more other rotational components of the gas turbine engine. The compressed air bleed arrangement takes a flow of compressed air from the compressor section along an off-take passage. The off-take passage opens in the compressor section at an off-take port. The off-take passage is rotatable, in use, with the rotational compressor components. The compressed air bleed arrangement is operable to provide the air in the off-take passage with higher static pressure than the air in the compressor section at the off-take port, by diffusing the air in the off-take passage. The off-take passage further includes off-take vanes, operable to increase the tangential velocity of the air in the off-take passage compared with the air at the off-take port.
摘要翻译：燃气涡轮发动机具有压缩机部分，其具有相对于静态压缩机部件旋转的旋转压缩机部件。提供压缩空气排出装置以冷却燃气涡轮发动机的一个或多个其它旋转部件。压缩空气排出装置沿着取出通道从压缩机部分流出压缩空气。取出通道在压缩机部分处于取出口处。取出通道在使用中与旋转压缩机部件一起是可旋转的。压缩空气排出装置可操作以通过使空气在取出通道中扩散而使取出通道中的空气具有比在取出口处的压缩机部分中的空气更高的静压。取出通道还包括离开叶片，其可操作以增加取出通道中的空气与取出口处的空气相切的切向速度。

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