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1. 发明授权

US08167545B2 Self-balancing face seals and gas turbine engine systems involving such seals 有权
标题翻译：自平衡面密封件和涉及这种密封件的燃气涡轮发动机系统
公开(公告)号：US08167545B2
公开(公告)日：2012-05-01
申请号：US12038127
申请日：2008-02-27
申请人： Jorn A. Glahn , Peter M. Munsell
发明人： Jorn A. Glahn , Peter M. Munsell
IPC分类号： F04D29/08 , F04D29/10
CPC分类号： F16J15/3472 , F01D11/001 , F01D11/003 , F01D11/025
摘要： Self-balancing face seals and gas turbine engine systems involving such seals are provided. In this regard, a representative self-balancing face seal assembly includes: a rotatable seal runner having a first seal runner face and an opposing second seal runner face; a first face seal operative to form a first seal with the first seal runner face, the first face seal being one of a hydrostatic seal and a hydrodynamic seal; and a second face seal operative to form a second seal with the second seal runner face, the first face seal being one of a hydrostatic seal and a hydrodynamic seal.
摘要翻译：提供了自平衡面密封件和涉及这种密封件的燃气涡轮发动机系统。在这方面，代表性的自平衡面密封组件包括：可旋转密封流道，其具有第一密封流道面和相对的第二密封流道面; 用于与第一密封流道面形成第一密封件的第一表面密封件，第一表面密封件是流体静力密封件和流体动力密封件之一; 以及第二面密封件，用于与所述第二密封流道面形成第二密封件，所述第一面密封件是静压密封件和流体动力密封件之一。

2. 发明申请

US20090047124A1 Gas Turbine Engine Systems Involving Hydrostatic Face Seals with Anti-Fouling Provisioning 有权
标题翻译：燃气轮机发动机系统涉及具有防污设备的静水面密封
公开(公告)号：US20090047124A1
公开(公告)日：2009-02-19
申请号：US11840645
申请日：2007-08-17
申请人： Jorn A. Glahn , Peter M. Munsell
发明人： Jorn A. Glahn , Peter M. Munsell
IPC分类号： F01D11/02 , F03B1/00
CPC分类号： F01D11/025 , F01D11/04 , F05D2300/224 , F16J15/342
摘要： Gas turbine engine systems involving hydrostatic face seals with anti-fouling provisioning are provided. In this regard, a representative turbine assembly for a gas turbine engine comprises: a turbine having a hydrostatic seal; the hydrostatic seal having a seal face, a seal runner, a carrier, and a biasing member; the seal face and the seal runner defining a high-pressure side and a lower-pressure side of the seal; the carrier being operative to position the seal face relative to the seal runner; and the biasing member being located on the lower-pressure side of the seal and being operative to bias the carrier such that interaction of the biasing member and gas pressure across the seal causes the carrier to position the seal face relative to the seal runner.
摘要翻译：提供了涉及具有防污供应的静水面密封件的燃气涡轮发动机系统。在这方面，用于燃气涡轮发动机的代表性涡轮组件包括：具有静水压密封的涡轮机; 静压密封件具有密封面，密封流道，载体和偏置构件; 密封面和密封流道限定密封件的高压侧和低压侧; 所述载体可操作以相对于所述密封流道定位所述密封面; 并且所述偏置构件位于所述密封件的低压侧上并且可操作以偏压所述载体，使得所述偏置构件与所述密封件之间的气体压力的相互作用使所述载体相对于所述密封流道定位所述密封面。

3. 发明授权

US07797941B2 Gas turbine engine systems involving hydrostatic face seals 有权
标题翻译：燃气涡轮发动机系统涉及静水面密封
公开(公告)号：US07797941B2
公开(公告)日：2010-09-21
申请号：US11924899
申请日：2007-10-26
申请人： Peter M. Munsell , Jorn A. Glahn
发明人： Peter M. Munsell , Jorn A. Glahn
IPC分类号： F02C1/00
CPC分类号： F01D11/04 , F01D11/025
摘要： Gas turbine engine systems involving hydrostatic face seals are provided. In this regard, representative compressor assembly for a gas turbine engine includes a compressor having a hydrostatic seal formed by a seal face and a seal runner.
摘要翻译：提供涉及静水面密封的燃气涡轮发动机系统。在这方面，用于燃气涡轮发动机的代表性压缩机组件包括具有由密封面和密封流道形成的静压密封的压缩机。

4. 发明授权

US08109717B2 Gas turbine engine systems involving hydrostatic face seals with integrated back-up seals 有权
标题翻译：燃气涡轮发动机系统涉及具有集成后备密封件的静水面密封
公开(公告)号：US08109717B2
公开(公告)日：2012-02-07
申请号：US11840636
申请日：2007-08-17
申请人： Jorn A. Glahn , Peter M. Munsell
发明人： Jorn A. Glahn , Peter M. Munsell
IPC分类号： F04D29/08
CPC分类号： F16J15/008 , F01D11/04 , F02C7/28 , F05D2240/55 , F05D2300/224 , F16J15/342
摘要： Gas turbine engine systems involving hydrostatic face seals with back-up seals are provided. In this regard, a representative seal assembly for a gas turbine engine includes: a hydrostatic seal having a seal face and a seal runner; and a back-up seal; wherein, in a normal mode of operation of the hydrostatic seal, interaction of the seal face and the seal runner maintains a pressure differential within the gas turbine engine and, in a failure mode of operation of the hydrostatic seal, the back-up seal maintains a pressure differential within the gas turbine engine.
摘要翻译：提供了涉及具有后备密封件的静水面密封件的燃气涡轮发动机系统。在这方面，用于燃气涡轮发动机的代表性密封组件包括：具有密封面和密封流道的静压密封件; 和备份密封件; 其中，在静压密封的正常操作模式中，密封面和密封流道的相互作用保持在燃气涡轮发动机内的压力差，并且在静水压密封的故障操作模式中，备用密封件保持燃气涡轮发动机内的压力差。

5. 发明申请

US20090047123A1 Gas Turbine Engine Systems Involving Hydrostatic Face Seals with Integrated Back-Up Seals 有权
标题翻译：燃气轮机发动机系统涉及具有集成后备密封件的静压面密封件
公开(公告)号：US20090047123A1
公开(公告)日：2009-02-19
申请号：US11840636
申请日：2007-08-17
申请人： Jorn A. Glahn , Peter M. Munsell
发明人： Jorn A. Glahn , Peter M. Munsell
IPC分类号： F01D11/00 , F03B1/00
CPC分类号： F16J15/008 , F01D11/04 , F02C7/28 , F05D2240/55 , F05D2300/224 , F16J15/342
摘要： Gas turbine engine systems involving hydrostatic face seals with back-up seals are provided. In this regard, a representative seal assembly for a gas turbine engine includes: a hydrostatic seal having a seal face and a seal runner; and a back-up seal; wherein, in a normal mode of operation of the hydrostatic seal, interaction of the seal face and the seal runner maintains a pressure differential within the gas turbine engine and, in a failure mode of operation of the hydrostatic seal, the back-up seal maintains a pressure differential within the gas turbine engine.
摘要翻译：提供了涉及具有后备密封件的静水面密封件的燃气涡轮发动机系统。在这方面，用于燃气涡轮发动机的代表性密封组件包括：具有密封面和密封流道的静压密封件; 和备份密封件; 其中，在静压密封的正常操作模式中，密封面和密封流道的相互作用保持在燃气涡轮发动机内的压力差，并且在静水压密封的故障操作模式中，备用密封件保持燃气涡轮发动机内的压力差。

6. 发明授权

US08459040B2 Rear hub cooling for high pressure compressor 有权
标题翻译：后轮毂冷却高压压缩机
公开(公告)号：US08459040B2
公开(公告)日：2013-06-11
申请号：US13544108
申请日：2012-07-09
申请人： Jorn A. Glahn , Peter M. Munsell , Steven B. Johnson
发明人： Jorn A. Glahn , Peter M. Munsell , Steven B. Johnson
IPC分类号： F02C6/08 , F02C7/141
CPC分类号： F01D5/081 , F01D9/065 , F02C6/08 , F02C7/143 , F02C7/185 , F04D29/321 , F04D29/5826 , F04D29/584 , F05D2220/3219 , F05D2260/205 , F05D2260/213
摘要： In one exemplary embodiment, a gas turbine engine includes a turbine and a high pressure compressor. The high pressure compressor includes a last stage having a last stage compressor blade and a last stage vane. The gas turbine engine includes a first flow path through which bleed air flows to the turbine and a second flow path through which air from the last stage of the high pressure compressor flows. The bleed air in the first flow path exchanges heat with a portion of the air in the second flow path in a heat exchanger to cool the air in the second flow path. The cooled air in the second flow path is returned to the high pressure compressor to cool the high pressure compressor.
摘要翻译：在一个示例性实施例中，燃气涡轮发动机包括涡轮机和高压压缩机。高压压缩机包括具有最后级压缩机叶片和最后级叶片的最后级。燃气涡轮发动机包括第一流动通道，排放空气通过该第一流动流向涡轮机，以及第二流动通道，来自高压压缩机最后一级的空气通过该流路流动。第一流路中的排出空气与热交换器中的第二流路中的空气的一部分进行热交换，以冷却第二流路中的空气。将第二流路中的冷却空气返回至高压压缩机，以冷却高压压缩机。

7. 发明授权

US08256229B2 Rear hub cooling for high pressure compressor 有权
标题翻译：后轮毂冷却高压压缩机
公开(公告)号：US08256229B2
公开(公告)日：2012-09-04
申请号：US12757450
申请日：2010-04-09
申请人： Jorn A. Glahn , Peter M. Munsell , Steven B. Johnson
发明人： Jorn A. Glahn , Peter M. Munsell , Steven B. Johnson
IPC分类号： F02C6/08
CPC分类号： F01D5/081 , F01D9/065 , F02C6/08 , F02C7/143 , F02C7/185 , F04D29/321 , F04D29/5826 , F04D29/584 , F05D2220/3219 , F05D2260/205 , F05D2260/213
摘要： In one exemplary embodiment, a gas turbine engine includes a turbine and a high pressure compressor. The high pressure compressor includes a last stage having a last stage compressor blade and a last stage vane. The gas turbine engine includes a first flow path through which bleed air flows to the turbine and a second flow path through which air from the last stage of the high pressure compressor flows. The bleed air in the first flow path exchanges heat with a portion of the air in the second flow path in a heat exchanger to cool the air in the second flow path. The cooled air in the second flow path is returned to the high pressure compressor to cool the high pressure compressor.
摘要翻译：在一个示例性实施例中，燃气涡轮发动机包括涡轮机和高压压缩机。高压压缩机包括具有最后级压缩机叶片和最后级叶片的最后级。燃气涡轮发动机包括第一流动通道，排放空气通过该第一流动流向涡轮机，以及第二流动通道，来自高压压缩机最后一级的空气通过该流路流动。第一流路中的排出空气与热交换器中的第二流路中的一部分空气进行热交换，以冷却第二流路中的空气。将第二流路中的冷却空气返回至高压压缩机，以冷却高压压缩机。

8. 发明申请

US20110247344A1 REAR HUB COOLING FOR HIGH PRESSURE COMPRESSOR 有权
标题翻译：后压缩机高压压缩机
公开(公告)号：US20110247344A1
公开(公告)日：2011-10-13
申请号：US12757450
申请日：2010-04-09
申请人： Jorn A. Glahn , Peter M. Munsell , Steven B. Johnson
发明人： Jorn A. Glahn , Peter M. Munsell , Steven B. Johnson
IPC分类号： F02C6/08 , F02C6/04
CPC分类号： F01D5/081 , F01D9/065 , F02C6/08 , F02C7/143 , F02C7/185 , F04D29/321 , F04D29/5826 , F04D29/584 , F05D2220/3219 , F05D2260/205 , F05D2260/213
摘要： In one exemplary embodiment, a gas turbine engine includes a turbine and a high pressure compressor. The high pressure compressor includes a last stage having a last stage compressor blade and a last stage vane. The gas turbine engine includes a first flow path through which bleed air flows to the turbine and a second flow path through which air from the last stage of the high pressure compressor flows. The bleed air in the first flow path exchanges heat with a portion of the air in the second flow path in a heat exchanger to cool the air in the second flow path. The cooled air in the second flow path is returned to the high pressure compressor to cool the high pressure compressor.
摘要翻译：在一个示例性实施例中，燃气涡轮发动机包括涡轮机和高压压缩机。高压压缩机包括具有最后级压缩机叶片和最后级叶片的最后级。燃气涡轮发动机包括第一流动通道，排放空气通过该第一流动流向涡轮机，以及第二流动通道，来自高压压缩机最后一级的空气通过该流路流动。第一流路中的排出空气与热交换器中的第二流路中的一部分空气进行热交换，以冷却第二流路中的空气。将第二流路中的冷却空气返回至高压压缩机，以冷却高压压缩机。

9. 发明申请

US20090051119A1 Gas Turbine Engine Systems Involving Hydrostatic Face Seals with Integrated Back-up Seals 有权
标题翻译：燃气轮机发动机系统涉及具有集成后备密封件的静压面密封件
公开(公告)号：US20090051119A1
公开(公告)日：2009-02-26
申请号：US11841124
申请日：2007-08-20
申请人： Jorn A. Glahn , Peter M. Munsell
发明人： Jorn A. Glahn , Peter M. Munsell
IPC分类号： F16J15/34 , F16J15/447
CPC分类号： F16J15/008 , F01D11/001 , F01D11/02 , F16J15/3464 , F16J15/4472
摘要： Gas turbine engine systems involving hydrostatic face seals with integrated back-up seals are provided. In this regard, a representative seal assembly for a gas turbine engine includes: a stator assembly and a rotor assembly configured to operatively engage each other to form a first seal and a second seal; the first seal being provided by a hydrostatic seal having a seal face and a seal runner; and the second seal being provided by a back-up seal such that responsive to a failure of the first seal, the back-up seal maintains at least a portion of a pressure differential established by the first seal prior to the failure.
摘要翻译：提供了包括具有集成后备密封件的静水面密封件的燃气涡轮发动机系统。在这方面，用于燃气涡轮发动机的代表性密封组件包括：定子组件和构造成可操作地彼此接合以形成第一密封件和第二密封件的转子组件; 第一密封件由具有密封面和密封流道的静水密封件提供; 并且所述第二密封件由备用密封件提供，使得响应于所述第一密封件的故障，所述后备密封件在所述故障之前保持由所述第一密封件建立的压差的至少一部分。

10. 发明申请

US20120282079A1 REAR HUB COOLING FOR HIGH PRESSURE COMPRESSOR 有权
标题翻译：后压缩机高压压缩机
公开(公告)号：US20120282079A1
公开(公告)日：2012-11-08
申请号：US13544108
申请日：2012-07-09
申请人： Jorn A. Glahn , Peter M. Munsell , Steven B. Johnson
发明人： Jorn A. Glahn , Peter M. Munsell , Steven B. Johnson
IPC分类号： F01D25/12 , F01D1/04 , F01D25/24
CPC分类号： F01D5/081 , F01D9/065 , F02C6/08 , F02C7/143 , F02C7/185 , F04D29/321 , F04D29/5826 , F04D29/584 , F05D2220/3219 , F05D2260/205 , F05D2260/213
摘要： In one exemplary embodiment, a gas turbine engine includes a turbine and a high pressure compressor. The high pressure compressor includes a last stage having a last stage compressor blade and a last stage vane. The gas turbine engine includes a first flow path through which bleed air flows to the turbine and a second flow path through which air from the last stage of the high pressure compressor flows. The bleed air in the first flow path exchanges heat with a portion of the air in the second flow path in a heat exchanger to cool the air in the second flow path. The cooled air in the second flow path is returned to the high pressure compressor to cool the high pressure compressor.
摘要翻译：在一个示例性实施例中，燃气涡轮发动机包括涡轮机和高压压缩机。高压压缩机包括具有最后级压缩机叶片和最后级叶片的最后级。燃气涡轮发动机包括第一流动通道，排放空气通过该第一流动流向涡轮机，以及第二流动通道，来自高压压缩机最后一级的空气通过该流路流动。第一流路中的排出空气与热交换器中的第二流路中的一部分空气进行热交换，以冷却第二流路中的空气。将第二流路中的冷却空气返回至高压压缩机，以冷却高压压缩机。

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