Patents by Inventor Brian H. Terpos
Brian H. Terpos has filed for patents to protect the following inventions. This listing includes patent applications that are pending as well as patents that have already been granted by the United States Patent and Trademark Office (USPTO).
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Patent number: 8920109Abstract: A thermal management arrangement (110) in a gas turbine engine (60), including: a conduit-arrangement (62) providing fluid communication between a compressor section (156) and: a relatively thermally responsive portion (52) of a turbine vane carrier (10); and a relatively thermally unresponsive portion (48) of a first turbine vane carrier. The conduit-arrangement includes: a general cooling flow outlet (122) disposed proximate the relatively thermally responsive portion of the turbine vane carrier and configured to discharge a general cooling flow (124); and an impingement flow outlet (118) disposed proximate the relatively thermally unresponsive portion and configured to discharge an impingement flow (120). The thermal management arrangement is configured such that a flow rate of the impingement flow is effective to accelerate a thermal response of the relatively thermally unresponsive portion toward a thermal response of the relatively thermally responsive portion.Type: GrantFiled: March 12, 2013Date of Patent: December 30, 2014Assignee: Siemens AktiengesellschaftInventors: Kok-Mun Tham, Ching-Pang Lee, Brian H. Terpos, Dustan M. Simko
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Patent number: 8893510Abstract: An air injection system for use in a gas turbine engine includes at least one outlet port through which air is extracted from the engine only during less than full load operation, at least one rotor cooling pipe, which is used to inject the air extracted from the outlet port(s) into a rotor chamber, a piping system that provides fluid communication between the one outlet port(s) and the rotor cooling pipe(s), a blower system for extracting air from the engine through the outlet port(s) and for conveying the extracted air through the piping system and the rotor cooling pipe(s) into the rotor chamber, and a valve system. The valve system is closed during full load engine operation to prevent air from passing through the piping system, and open during less than full load engine operation to allow air to pass through the piping system.Type: GrantFiled: November 7, 2012Date of Patent: November 25, 2014Assignee: Siemens AktiengesellschaftInventors: Kok-Mun Tham, Ching-Pang Lee, Brian H. Terpos, Dustan M. Simko
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Publication number: 20140271103Abstract: A thermal management arrangement (110) in a gas turbine engine (60), including: a conduit-arrangement (62) providing fluid communication between a compressor section (156) and: a relatively thermally responsive portion (52) of a turbine vane carrier (10); and a relatively thermally unresponsive portion (48) of a first turbine vane carrier. The conduit-arrangement includes: a general cooling flow outlet (122) disposed proximate the relatively thermally responsive portion of the turbine vane carrier and configured to discharge a general cooling flow (124); and an impingement flow outlet (118) disposed proximate the relatively thermally unresponsive portion and configured to discharge an impingement flow (120). The thermal management arrangement is configured such that a flow rate of the impingement flow is effective to accelerate a thermal response of the relatively thermally unresponsive portion toward a thermal response of the relatively thermally responsive portion.Type: ApplicationFiled: March 12, 2013Publication date: September 18, 2014Inventors: Kok-Mun Tham, Ching-Pang Lee, Brian H. Terpos, Dustan M. Simko
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Patent number: 8721278Abstract: A flange connection for an exhaust section of a gas turbine engine. The flange connection includes a stub flange attached to an exhaust manifold. The stub flange has a first axial face for engagement with the axial face of a cylinder flange extending radially from an exhaust cylinder. A plate structure attached to the cylinder flange is configured to provide axial retention of the stub flange to the axial face of the cylinder flange. The plate structure includes a resilient beam portion extending radially inwardly and engaging a second axial face of the stub flange. The stub flange is retained between the cylinder flange and the beam portion of the plate structure in an interference fit to provide three degrees of freedom of the stub flange relative to the exhaust cylinder.Type: GrantFiled: March 11, 2011Date of Patent: May 13, 2014Assignee: Siemens Energy, Inc.Inventors: Yevgeniy Shteyman, James Marshall, Brian Micklos, Jonathan Leagon, Christopher Scogin, Brian H. Terpos, Robert T. Brooks, Scott Smith, Robert W. Spitzer, David Wiebe
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Publication number: 20140123675Abstract: An air injection system for use in a gas turbine engine includes at least one outlet port through which air is extracted from the engine only during less than full load operation, at least one rotor cooling pipe, which is used to inject the air extracted from the outlet port(s) into a rotor chamber, a piping system that provides fluid communication between the one outlet port(s) and the rotor cooling pipe(s), a blower system for extracting air from the engine through the outlet port(s) and for conveying the extracted air through the piping system and the rotor cooling pipe(s) into the rotor chamber, and a valve system. The valve system is closed during full load engine operation to prevent air from passing through the piping system, and open during less than full load engine operation to allow air to pass through the piping system.Type: ApplicationFiled: November 7, 2012Publication date: May 8, 2014Inventors: Kok-Mun Tham, Ching-Pang Lee, Brian H. Terpos, Dustan M. Simko
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Publication number: 20120023968Abstract: A flange connection for an exhaust section of a gas turbine engine. The flange connection includes a stub flange attached to an exhaust manifold. The stub flange has a first axial face for engagement with the axial face of a cylinder flange extending radially from an exhaust cylinder. A plate structure attached to the cylinder flange is configured to provide axial retention of the stub flange to the axial face of the cylinder flange. The plate structure includes a resilient beam portion extending radially inwardly and engaging a second axial face of the stub flange. The stub flange is retained between the cylinder flange and the beam portion of the plate structure in an interference fit to provide three degrees of freedom of the stub flange relative to the exhaust cylinder.Type: ApplicationFiled: March 11, 2011Publication date: February 2, 2012Inventors: Yevgeniy Shteyman, James Marshall, Brian Micklos, Jonathan Leagon, Christopher Scogin, Brian H. Terpos, Robert T. Brooks, Scott Smith, Robert W. Spitzer, David Wiebe
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Patent number: 7686575Abstract: An inner mounting ring (20) for gas turbine flow path components such as shroud ring segments (24). The inner ring (20) may be mounted to an outer ring (22) on radially slidable mounts (26, 28) that maintain the two rings (20, 22) in coaxial relationship, but allows them to thermally expand at different rates. This allows matching of the radial expansion rate of the inner ring (20) to that of the turbine blade tips (32), thus providing reduced clearance (33) between the turbine blade tips (32) and the inner surface of the shroud ring segments (24) under all engine operating conditions. The inner ring (20) may be made of a material with a lower coefficient of thermal expansion than that of the outer ring (22).Type: GrantFiled: August 17, 2006Date of Patent: March 30, 2010Assignee: Siemens Energy, Inc.Inventors: Abdullatif M. Chehab, Scott T. Waechter, Kevin M. Light, Brian H. Terpos, Zhengxiang Pu
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Publication number: 20100031671Abstract: An inner mounting ring (20) for gas turbine flow path components such as shroud ring segments (24). The inner ring (20) may be mounted to an outer ring (22) on radially slidable mounts (26, 28) that maintain the two rings (20, 22) in coaxial relationship, but allows them to thermally expand at different rates. This allows matching of the radial expansion rate of the inner ring (20) to that of the turbine blade tips (32), thus providing reduced clearance (33) between the turbine blade tips (32) and the inner surface of the shroud ring segments (24) under all engine operating conditions. The inner ring (20) may be made of a material with a lower coefficient of thermal expansion than that of the outer ring (22).Type: ApplicationFiled: August 17, 2006Publication date: February 11, 2010Inventors: Abdullatif M. Chehab, Scott T. Waechter, Kevin M. Light, Brian H. Terpos, Zhengxiang Pu
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Patent number: 5601401Abstract: An apparatus for actuating variable stage vanes is provided having a plurality of pivot arms, a synchronizing ring, and apparatus for pivotly attaching the pivot arms to the synchronizing ring. Each pivot arm includes a first end for fixed attachment with one of the vanes. The synchronizing ring includes a first flange, a second flange, a web extending between the flanges, and a plurality of openings disposed in the web. The apparatus for pivotly attaching the pivot arms to the synchronizing ring are disposed within the openings.Type: GrantFiled: December 21, 1995Date of Patent: February 11, 1997Assignee: United Technologies CorporationInventors: Alfred P. Matheny, Brian H. Terpos