Patents by Inventor Paul W. Duesler
Paul W. Duesler 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: 11572928Abstract: A heat exchanger (HEX) for cooling air in a gas turbine engine is provided. An adjustable damper is provided. The adjustable damper may be for damping a movement of the HEX relative to the gas turbine engine. An adjustable damper may comprise: a first tube; a second tube located at least partially within the first tube; a housing coupled to the second tube; a moveable member, the moveable member comprising a contacting surface in contact with the second tube; an adjusting member adjustably coupled to the housing; and a spring member located between the moveable member and the adjusting member, the spring member configured to at least one of compress or decompress in response to adjusting member moving relative to the housing.Type: GrantFiled: February 19, 2019Date of Patent: February 7, 2023Assignee: Raytheon Technologies CorporationInventors: Paul W. Duesler, Frederick M. Schwarz
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Patent number: 11492973Abstract: A heat exchanger (HEX) for cooling air in a gas turbine engine is provided. The HEX may comprise a central manifold comprising an inlet portion, a first outlet portion, and a second outlet portion. The HEX may further comprise a plurality of tubes coupled to the central manifold, the plurality of tubes comprising at least a first tube, a second tube, a third tube, and a fourth tube, a shroud at least partially encasing said plurality of tubes, and a cooling air flow path defined by at least one of the shroud, the plurality of tubes, and an outer surface of the central manifold, wherein the cooling air flow path is orthogonal to said plurality of tubes.Type: GrantFiled: March 26, 2019Date of Patent: November 8, 2022Assignee: Raytheon Technologies CorporationInventors: Paul W. Duesler, Frederick M. Schwarz
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Patent number: 11421598Abstract: A heat exchanger array includes a first row of heat exchangers, a second row of heat exchangers, and side curtains. The first row heat exchangers are spaced apart to define first gaps. The second row heat exchangers are spaced apart to define second gaps and are positioned downstream of and staggered from the first row heat exchangers such that the second row heat exchangers are aligned with the first gaps and the first row heat exchangers are aligned with the second gaps. Each side curtain is in close proximity to a first row heat exchanger and a second row heat exchanger. The side curtains define a neck region upstream of and aligned with each first row heat exchanger and each second row heat exchanger. Each neck region has a neck area that is less than a frontal area of the heat exchanger with which it is aligned.Type: GrantFiled: February 4, 2020Date of Patent: August 23, 2022Assignee: Raytheon Technologies CorporationInventors: Paul W. Duesler, Frederick M. Schwarz
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Patent number: 11408300Abstract: A gas turbine engine may include a rotor overspeed protection (ROP) assembly. The ROP assembly may include an annular blade outer air seal (BOAS) assembly including a ROP segment. The ROP assembly may include a stator vane coupled with the BOAS assembly/. The stator vane may include a stator flange disposed about a forward edge portion of the stator vane. The ROP segment may include a ROP flange extending in an axially aft direction from a main body of the ROP segment toward the stator vane, wherein the ROP flange is disposed radially inward of the stator flange.Type: GrantFiled: December 3, 2018Date of Patent: August 9, 2022Assignee: Raytheon Technologies CorporationInventors: Brian Merry, Paul W. Duesler
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Patent number: 11174757Abstract: An assembly is provided for a turbine engine with an axial centerline. This assembly includes a turbine engine structure and a valve assembly. The turbine engine structure includes an outer duct wall, an inner duct wall, a first flow path and a second flow path. The inner duct wall is radially inward of the outer duct wall. The first flow path is radially inward of the inner duct wall. The second flow path is radially outward of the inner duct wall and is radially inward of the outer duct wall. The valve assembly includes a valve element and a valve actuator. The valve element is configured to regulate flow of fluid between the first flow path and the second flow path. The valve actuator is configured to move the valve element. The valve actuator is positioned entirely radially outward of the outer duct wall.Type: GrantFiled: January 20, 2020Date of Patent: November 16, 2021Assignee: Raytheon Technologies CorporationInventors: Joseph N. Cerino, Andrew Yanaros, Paul W. Duesler
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Publication number: 20210222587Abstract: An assembly is provided for a turbine engine with an axial centerline. This assembly includes a turbine engine structure and a valve assembly. The turbine engine structure includes an outer duct wall, an inner duct wall, a first flow path and a second flow path. The inner duct wall is radially inward of the outer duct wall. The first flow path is radially inward of the inner duct wall. The second flow path is radially outward of the inner duct wall and is radially inward of the outer duct wall. The valve assembly includes a valve element and a valve actuator. The valve element is configured to regulate flow of fluid between the first flow path and the second flow path. The valve actuator is configured to move the valve element. The valve actuator is positioned entirely radially outward of the outer duct wall.Type: ApplicationFiled: January 20, 2020Publication date: July 22, 2021Inventors: Joseph N. Cerino, Andrew Yanaros, Paul W. Duesler
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Patent number: 11041677Abstract: Aspects of the disclosure are directed to a heat exchanger comprising: a first plurality of channels configured to convey a first medium at a first set of temperatures along a first span of the first plurality of channels, the first set of temperatures including a first inlet temperature and a first outlet temperature, a second plurality of channels configured to convey a second medium at a second set of temperatures along a second span of the second plurality of channels, the second set of temperatures being at least partially different from the first set of temperatures and including a second inlet temperature and a second outlet temperature, and a core region where the first plurality of channels and the second plurality of channels are co-mingled with respect to one another.Type: GrantFiled: January 4, 2016Date of Patent: June 22, 2021Assignee: Raytheon Technologies CorporationInventors: Paul W. Duesler, Joseph W. Bridges, Jr.
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Patent number: 10982595Abstract: A gas turbine engine has a compressor section including a lower pressure compressor and a higher pressure compressor, and a turbine section. A core engine housing surrounds the compressor section and the turbine section. An outer intermediate housing wall defines an internal chamber between the core housing and the outer intermediate housing. A fan rotor and a fan casing surround the fan rotor to define a bypass duct between the fan case and the outer intermediate housing. A heat exchanger is mounted in the internal chamber and receives high pressure air for cooling the high pressure air and delivering the high pressure air into the core engine housing to be utilized as cooling air for a component. Air from the lower pressure compressor is utilized to cool the higher pressure air in the heat exchanger.Type: GrantFiled: August 23, 2016Date of Patent: April 20, 2021Assignee: Raytheon Technologies CorporationInventors: Frederick M. Schwarz, Paul W. Duesler
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Patent number: 10830086Abstract: A cam isolation system for a gas turbine engine compressor actuator includes a torque tube. The system also includes a cam bracket operatively coupled to an engine case structure, the cam bracket defining a slot. The system further includes an actuator bracket operatively coupled to the torque tube at a first end of the actuator bracket, the actuator bracket having a pin disposed within the slot of the cam bracket.Type: GrantFiled: July 18, 2018Date of Patent: November 10, 2020Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: William S. Pratt, Paul W. Duesler
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Patent number: 10794288Abstract: An exemplary gas turbine engine includes a fan bypass duct defined between a fan nacelle and core cowl of an engine core. The engine core includes a cooled cooling air system configured to receive cooling air from a primary flowpath bleed at a diffuser within the engine core and configured to provide cooled cooling air to at least one component within the engine core. The cooled cooling air system including an air-air heat exchanger.Type: GrantFiled: July 7, 2015Date of Patent: October 6, 2020Assignee: Raytheon Technologies CorporationInventors: Frederick M. Schwarz, Paul W. Duesler
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Publication number: 20200248625Abstract: A heat exchanger array includes a first row of heat exchangers, a second row of heat exchangers, and side curtains. The first row heat exchangers are spaced apart to define first gaps. The second row heat exchangers are spaced apart to define second gaps and are positioned downstream of and staggered from the first row heat exchangers such that the second row heat exchangers are aligned with the first gaps and the first row heat exchangers are aligned with the second gaps. Each side curtain is in close proximity to a first row heat exchanger and a second row heat exchanger. The side curtains define a neck region upstream of and aligned with each first row heat exchanger and each second row heat exchanger. Each neck region has a neck area that is less than a frontal area of the heat exchanger with which it is aligned.Type: ApplicationFiled: February 4, 2020Publication date: August 6, 2020Inventors: Paul W. Duesler, Frederick M. Schwarz
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Publication number: 20200240280Abstract: A slider seal assembly for a gas turbine engine, comprising a housing comprising an outer surface and an inner surface, and a recessed opening between the inner surface and the outer surface, wherein the inner surface of the housing includes a flat portion configured to match a receiver on an inner wall of a casing of the gas turbine engine; a seal plate received within the recessed opening and moveable relative to the housing; and a retaining ring configured to retain the seal plate adjacent the housing, the retaining ring includes a plurality of tabs configured to retain the seal plate adjacent the housing.Type: ApplicationFiled: January 29, 2019Publication date: July 30, 2020Applicant: United Technologies CorporationInventors: Curtis C. Cowan, Paul W. Duesler, Michael R. Thomas, Michael Joseph Murphy
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Publication number: 20200173297Abstract: A gas turbine engine may include a rotor overspeed protection (ROP) assembly. The ROP assembly may include an annular blade outer air seal (BOAS) assembly including a ROP segment. The ROP assembly may include a stator vane coupled with the BOAS assembly/. The stator vane may include a stator flange disposed about a forward edge portion of the stator vane. The ROP segment may include a ROP flange extending in an axially aft direction from a main body of the ROP segment toward the stator vane, wherein the ROP flange is disposed radially inward of the stator flange.Type: ApplicationFiled: December 3, 2018Publication date: June 4, 2020Applicant: UNITED TECHNOLOGIES CORPORATIONInventors: Brian Merry, Paul W. Duesler
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Patent number: 10563582Abstract: A heat exchanger array includes a first row of heat exchangers, a second row of heat exchangers, and side curtains. The first row heat exchangers are spaced apart to define first gaps. The second row heat exchangers are spaced apart to define second gaps and are positioned downstream of and staggered from the first row heat exchangers such that the second row heat exchangers are aligned with the first gaps and the first row heat exchangers are aligned with the second gaps. Each side curtain is in close proximity to a first row heat exchanger and a second row heat exchanger. The side curtains define a neck region upstream of and aligned with each first row heat exchanger and each second row heat exchanger. Each neck region has a neck area that is less than a frontal area of the heat exchanger with which it is aligned.Type: GrantFiled: January 19, 2016Date of Patent: February 18, 2020Assignee: United Technologies CorporationInventors: Paul W. Duesler, Frederick M. Schwarz
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Publication number: 20200025023Abstract: A cam isolation system for a gas turbine engine compressor actuator includes a torque tube. The system also includes a cam bracket operatively coupled to an engine case structure, the cam bracket defining a slot. The system further includes an actuator bracket operatively coupled to the torque tube at a first end of the actuator bracket, the actuator bracket having a pin disposed within the slot of the cam bracket.Type: ApplicationFiled: July 18, 2018Publication date: January 23, 2020Inventors: William S. Pratt, Paul W. Duesler
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Patent number: 10526916Abstract: A heat exchanger for use in a gas turbine engine has a central body including an inlet manifold and at least one tube providing an outlet manifold, and a plurality of tubes communicating holes in an outer periphery of the inlet manifold to holes in an outer periphery of the outlet manifold, and passages for cooling air to pass across the tubes. A gas turbine engine is also disclosed.Type: GrantFiled: April 26, 2016Date of Patent: January 7, 2020Assignee: United Technologies CorporationInventors: Frederick M. Schwarz, Paul W. Duesler
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Patent number: 10436115Abstract: A gas turbine engine has a core engine with a compressor section and a turbine section. The compressor section includes a low pressure compressor and a high pressure compressor. A cooling air system taps compressed air and passes the compressed air through a heat exchanger. Cooling air passes over the heat exchanger to cool the compressed air, which is returned to the core engine to provide a cooling function. The heat exchanger is mounted through a flexible mount allowing movement between a static structure and the heat exchanger.Type: GrantFiled: August 22, 2016Date of Patent: October 8, 2019Assignee: United Technologies CorporationInventors: Paul W. Duesler, Frederick M. Schwarz
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Publication number: 20190218974Abstract: A heat exchanger (HEX) for cooling air in a gas turbine engine is provided. The HEX may comprise a central manifold comprising an inlet portion, a first outlet portion, and a second outlet portion. The HEX may further comprise a plurality of tubes coupled to the central manifold, the plurality of tubes comprising at least a first tube, a second tube, a third tube, and a fourth tube, a shroud at least partially encasing said plurality of tubes, and a cooling air flow path defined by at least one of the shroud, the plurality of tubes, and an outer surface of the central manifold, wherein the cooling air flow path is orthogonal to said plurality of tubes.Type: ApplicationFiled: March 26, 2019Publication date: July 18, 2019Applicant: UNITED TECHNOLOGIES CORPORATIONInventors: Paul W. Duesler, Frederick M. Schwarz
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Publication number: 20190178164Abstract: A heat exchanger (HEX) for cooling air in a gas turbine engine is provided. An adjustable damper is provided. The adjustable damper may be for damping a movement of the HEX relative to the gas turbine engine. An adjustable damper may comprise: a first tube; a second tube located at least partially within the first tube; a housing coupled to the second tube; a moveable member, the moveable member comprising a contacting surface in contact with the second tube; an adjusting member adjustably coupled to the housing; and a spring member located between the moveable member and the adjusting member, the spring member configured to at least one of compress or decompress in response to adjusting member moving relative to the housing.Type: ApplicationFiled: February 19, 2019Publication date: June 13, 2019Applicant: United Technologies CorporationInventors: Paul W. Duesler, Frederick M. Schwarz
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Patent number: 10287982Abstract: A heat exchanger (HEX) for cooling air in a gas turbine engine is provided. The HEX may comprise a central manifold comprising an inlet portion, a first outlet portion, and a second outlet portion. The HEX may further comprise a plurality of tubes coupled to the central manifold, the plurality of tubes comprising at least a first tube, a second tube, a third tube, and a fourth tube, a shroud at least partially encasing said plurality of tubes, and a cooling air flow path defined by at least one of the shroud, the plurality of tubes, and an outer surface of the central manifold, wherein the cooling air flow path is orthogonal to said plurality of tubes.Type: GrantFiled: August 14, 2015Date of Patent: May 14, 2019Assignee: United Technologies CorporationInventors: Paul W. Duesler, Frederick M. Schwarz