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1. 发明授权

US10119468B2 Customer bleed air pressure loss reduction 有权
公开(公告)号：US10119468B2
公开(公告)日：2018-11-06
申请号：US13366597
申请日：2012-02-06
申请人： Cheng-Zhang Wang , Thomas G. Phillips , David F. Cloud , Peter M. Munsell
发明人： Cheng-Zhang Wang , Thomas G. Phillips , David F. Cloud , Peter M. Munsell
IPC分类号： F02C6/08 , F01D9/02 , F01D9/06 , F02C7/18 , F02C9/18
摘要： A bleed air supply system for a gas turbine engine comprising a duct having an inlet end and extending to an outlet end. The inlet end of the duct is provided with a central insert. In another feature, there may be a plurality of ducts, and inlet ends of the plurality of ducts being spaced by at least 90°. In another feature, a compressor may have a diffuser with a shroud ending upstream of the downstream end of an inner shroud, having an outer shroud ending at a location upstream of a downstream end of an inner shroud at locations circumferentially aligned with an inlet end of the duct.

2. 发明申请

US20130199205A1 CUSTOMER BLEED AIR PRESSURE LOSS REDUCTION 审中-公开
标题翻译：客户BLEED AIR PRESSURE LOSS REDUCTION
公开(公告)号：US20130199205A1
公开(公告)日：2013-08-08
申请号：US13366597
申请日：2012-02-06
申请人： Cheng-Zhang Wang , Thomas G. Phillips , David F. Cloud , Peter M. Munsell
发明人： Cheng-Zhang Wang , Thomas G. Phillips , David F. Cloud , Peter M. Munsell
IPC分类号： F02C6/08
CPC分类号： F02C6/08 , F01D9/023 , F01D9/065 , F02C7/185 , F02C9/18 , F05D2260/601 , F05D2270/17 , F05D2270/301 , Y02T50/675
摘要： A bleed air supply system for a gas turbine engine comprising a duct having an inlet end and extending to an outlet end. The inlet end of the duct is provided with a central insert. In another feature, there may be a plurality of ducts, and inlet ends of the plurality of ducts being spaced by at least 90°. In another feature, a compressor may have a diffuser with a shroud ending upstream of the downstream end of an inner shroud, having an outer shroud ending at a location upstream of a downstream end of an inner shroud at locations circumferentially aligned with an inlet end of the duct.
摘要翻译：一种用于燃气涡轮发动机的放气系统，包括具有入口端并延伸到出口端的管道。管道的入口端设置有中心插入件。在另一个特征中，可以存在多个管道，并且多个管道的入口端部至少间隔开90°。在另一个特征中，压缩机可以具有扩散器，其具有在内护罩的下游端的上游的护罩，其具有外护罩，其终止于在内护罩的下游端的上游的位置，管道。

3. 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。

4. 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。

5. 发明授权

US10724431B2 Buffer system that communicates buffer supply air to one or more portions of a gas turbine engine 有权
公开(公告)号：US10724431B2
公开(公告)日：2020-07-28
申请号：US13362330
申请日：2012-01-31
申请人： Peter M. Munsell , Philip S. Stripinis
发明人： Peter M. Munsell , Philip S. Stripinis
IPC分类号： F02C6/08 , F01D25/12 , F02C7/18 , F01D25/18
摘要： A gas turbine engine includes a buffer system that communicates a buffer supply air to a portion of the gas turbine engine. The buffer system includes a first bleed air supply having a first pressure, a second bleed air supply having a second pressure that is greater than the first pressure, and a valve that selects between the first bleed air supply and the second bleed air supply to communicate the buffer supply air to the portion of the gas turbine engine.

6. 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。

7. 发明授权

US06663346B2 Compressor stator inner diameter platform bleed system 有权
公开(公告)号：US06663346B2
公开(公告)日：2003-12-16
申请号：US10053432
申请日：2002-01-17
申请人： Peter M. Munsell , Bruce P Biederman , Matthew D Nicolson , David P. Dube
发明人： Peter M. Munsell , Bruce P Biederman , Matthew D Nicolson , David P. Dube
IPC分类号： F01D906
CPC分类号： F04D29/542 , B64D13/00 , B64D13/006 , F02C6/08
摘要： The present invention relates to a bleed system for use in a gas turbine engine. The bleed system comprises a plurality of blades with each of the blades having an airfoil member and a platform structure. The bleed system further has at least one interblade passage formed by adjacent ones of the airfoil members and an inner endwall formed by the platform structures. A bleed hole is located in the at least one interblade passage for extracting a portion of a fluid passing therethrough. The bleed positioning within the stator passage, both axially and circumferentially, is selected for optimum balance of static pressure and tangential velocity.

8. 发明申请

US20130192251A1 BUFFER SYSTEM THAT COMMUNICATES BUFFER SUPPLY AIR TO ONE OR MORE PORTIONS OF A GAS TURBINE ENGINE 审中-公开
标题翻译：缓冲器系统，通信缓冲器供应到一个或多个气体涡轮发动机的部分
公开(公告)号：US20130192251A1
公开(公告)日：2013-08-01
申请号：US13362307
申请日：2012-01-31
申请人： Peter M. Munsell , Philip S. Stripinis
发明人： Peter M. Munsell , Philip S. Stripinis
IPC分类号： F02C6/08
CPC分类号： F02C6/08 , F01D11/04 , F01D11/06 , F01D25/125 , F02C7/06 , F02C7/28 , F02C9/18 , F05D2260/601 , Y02T50/675 , Y10T29/49323
摘要： A gas turbine engine includes a buffer system that can communicate a buffer supply air to a portion of the gas turbine engine. The buffer system includes a first bleed air supply having a first pressure, a second bleed air supply having a second pressure that is greater than the first pressure, and an ejector that selectively augments the first bleed air supply to prepare the buffer supply air for communication to the portion of the gas turbine engine.
摘要翻译：燃气涡轮发动机包括缓冲系统，该缓冲系统可将缓冲器供给空气传送到燃气涡轮发动机的一部分。缓冲系统包括具有第一压力的第一排气源，具有大于第一压力的第二压力的第二排放空气源，以及选择性地增加第一排气供应以准备用于通信的缓冲器供应空气的喷射器到燃气涡轮发动机的部分。

9. 发明申请

US20130177385A1 GAS TURBINE ENGINE FORWARD BEARING COMPARTMENT ARCHITECTURE 有权
公开(公告)号：US20130177385A1
公开(公告)日：2013-07-11
申请号：US13346832
申请日：2012-01-10
申请人： Peter M. Munsell , Philip S. Stripinis
发明人： Peter M. Munsell , Philip S. Stripinis
IPC分类号： F01D25/16
CPC分类号： F02C7/06 , F01D25/16 , F02C7/12 , F02C7/28 , F02C7/36 , F02K3/06
摘要： A gas turbine engine includes a bearing structure mounted to the front center body case structure to rotationally support a shaft driven by a geared architecture. A bearing compartment passage structure is in communication with the bearing structure through a front center body case structure.

10. 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。

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