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1. 发明申请

US20120301276A1 WEAR PIN GAP CLOSURE DETECTION SYSTEM FOR GAS TURBINE ENGINE 有权
标题翻译：用于气体发动机的密封挡圈闭合检测系统
公开(公告)号：US20120301276A1
公开(公告)日：2012-11-29
申请号：US13113351
申请日：2011-05-23
申请人： Ram Bahadur Singh , David L. Wasdell , Keith A Miller
发明人： Ram Bahadur Singh , David L. Wasdell , Keith A Miller
IPC分类号： F01D25/00
CPC分类号： F01D11/001 , F01D21/04 , F04D27/008 , F04D27/0292 , F05D2240/55 , F05D2250/32 , F05D2260/30 , F05D2260/36 , F05D2260/80
摘要： A wear indication system for use in turbine engines to measure the rate of gap closure between a seal holder and a rotor disk in a compressor blade assembly is disclosed. The wear indication system may include a support system capable of supporting a wear indicator formed from a relatively soft wear material without enabling the wear indicator to shift position or to fall out. One or more wear pins may be releasably attached to a compression plate with a seal holder. The seal holder may restrain the wear pin in position in an interference fit. During turbine engine operation, the wear pin is used to determine the rate of gap closing between a rotor disk and a seal holder precisely so that gas turbine engine repair can be scheduled and proper actions be taken to prevent rubbing between rotating and stationary parts of a compressor.
摘要翻译：公开了一种用于涡轮发动机中的磨损指示系统，以测量压缩机叶片组件中的密封保持器和转子盘之间的间隙关闭速率。磨损指示系统可以包括能够支撑由相对软的磨损材料形成的磨损指示器而不使磨损指示器移位或脱落的支撑系统。一个或多个磨损销可以用密封保持器可释放地附接到压缩板。密封保持器可以将磨损销限制在过盈配合中的适当位置。在涡轮发动机运行期间，磨损销用于确定转子盘和密封保持器之间的间隙关闭速率，以便能够安排燃气涡轮发动机修理，并采取适当的措施，以防止摩擦和旋转部件之间的摩擦压缩机。

2. 发明授权

US08864446B2 Wear pin gap closure detection system for gas turbine engine 有权
标题翻译：用于燃气轮机的磨针闭合检测系统
公开(公告)号：US08864446B2
公开(公告)日：2014-10-21
申请号：US13113351
申请日：2011-05-23
申请人： Ram Bahadur Singh , David L. Wasdell , Keith A Miller
发明人： Ram Bahadur Singh , David L. Wasdell , Keith A Miller
IPC分类号： F01D25/00 , F04D27/00 , F01D11/00 , F01D21/04
CPC分类号： F01D11/001 , F01D21/04 , F04D27/008 , F04D27/0292 , F05D2240/55 , F05D2250/32 , F05D2260/30 , F05D2260/36 , F05D2260/80
摘要： A wear indication system for use in turbine engines to measure the rate of gap closure between a seal holder and a rotor disk in a compressor blade assembly is disclosed. The wear indication system may include a support system capable of supporting a wear indicator formed from a relatively soft wear material without enabling the wear indicator to shift position or to fall out. One or more wear pins may be releasably attached to a compression plate with a seal holder. The seal holder may restrain the wear pin in position in an interference fit. During turbine engine operation, the wear pin is used to determine the rate of gap closing between a rotor disk and a seal holder precisely so that gas turbine engine repair can be scheduled and proper actions be taken to prevent rubbing between rotating and stationary parts of a compressor.
摘要翻译：公开了一种用于涡轮发动机中的磨损指示系统，以测量压缩机叶片组件中的密封保持器和转子盘之间的间隙关闭速率。磨损指示系统可以包括能够支撑由相对软的磨损材料形成的磨损指示器而不使磨损指示器移位或脱落的支撑系统。一个或多个磨损销可以用密封保持器可释放地附接到压缩板。密封保持器可以将磨损销限制在过盈配合中的适当位置。在涡轮发动机运行期间，磨损销用于确定转子盘和密封保持器之间的间隙关闭速率，以便能够安排燃气涡轮发动机修理，并采取适当的措施，以防止摩擦和旋转部件之间的摩擦压缩机。

3. 发明申请

US20130224009A1 MID-SECTION OF A CAN-ANNULAR GAS TURBINE ENGINE WITH A RADIAL AIR FLOW DISCHARGED FROM THE COMPRESSOR SECTION 有权
标题翻译：具有从压缩机部分排出的径向空气流的CAN-ANNULAR气体涡轮发动机的中间部分
公开(公告)号：US20130224009A1
公开(公告)日：2013-08-29
申请号：US13408147
申请日：2012-02-29
申请人： David A. Little , Gerard McQuiggan , David L. Wasdell
发明人： David A. Little , Gerard McQuiggan , David L. Wasdell
IPC分类号： F01D1/04 , F01D25/00
CPC分类号： F02C3/14
摘要： A midframe portion (213) of a gas turbine engine (210) is presented, and includes a compressor section (212) configured to discharge an air flow (211) directed in a radial direction from an outlet of the compressor section (212). Additionally, the midframe portion (213) includes a manifold (214) to directly couple the air flow (211) from the compressor section (212) outlet to an inlet of a respective combustor head (218) of the midframe portion (213).
摘要翻译：呈现燃气涡轮发动机（210）的中架部分（213），并且包括被配置为从压缩机部分（212）的出口排出径向指向的空气流（211）的压缩机部分（212）。另外，中架部分（213）包括将空气流（211）从压缩机部分（212）出口直接联接到中架部分（213）的相应燃烧器头部（218）的入口的歧管（214）。

4. 发明授权

US09476355B2 Mid-section of a can-annular gas turbine engine with a radial air flow discharged from the compressor section 有权
标题翻译：具有从压缩机部分排放的径向气流的罐环式燃气涡轮发动机的中部
公开(公告)号：US09476355B2
公开(公告)日：2016-10-25
申请号：US13408147
申请日：2012-02-29
申请人： David A. Little , Gerard McQuiggan , David L. Wasdell
发明人： David A. Little , Gerard McQuiggan , David L. Wasdell
IPC分类号： F02C3/08 , F23R3/04 , F02C3/14
CPC分类号： F02C3/14
摘要： A midframe portion (213) of a gas turbine engine (210) is presented, and includes a compressor section (212) configured to discharge an air flow (211) directed in a radial direction from an outlet of the compressor section (212). Additionally, the midframe portion (213) includes a manifold (214) to directly couple the air flow (211) from the compressor section (212) outlet to an inlet of a respective combustor head (218) of the midframe portion (213).
摘要翻译：呈现燃气涡轮发动机（210）的中架部分（213），并且包括被配置为从压缩机部分（212）的出口排出径向指向的空气流（211）的压缩机部分（212）。另外，中框部分（213）包括将空气流（211）从压缩机部分（212）出口直接联接到中架部分（213）的相应燃烧器头部（218）的入口的歧管（214）。

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