Patents by Inventor David C. Pimenta
David C. Pimenta 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: 10302041Abstract: Tracks (35), fastened to static structure of an aircraft engine nozzle, guide sliders (32) journaled in struts (27, 28) fastened to a flap (23) of the nozzle. Each slider and attached journal axle or bolt (33) is formed of cobalt, and each track slider surface (61) and journal bushings (43, 44) are formed of a nickel alloy to reduce wear from rubbing. Track slides (40, 41) are mounted to the static structure of the nozzle by blind bolts (68) having a tool recess (70) at its threaded tip to prevent the bolt (68) from turning as a nut is secured. Each slider has limited rotation due to a pin (102), thereon engaging a slot in a tab (100) of the bushing (43) to assist in inserting the slider (32) into the beveled ends of the tracks (35, 36), when mounting or replacing a flap.Type: GrantFiled: December 9, 2016Date of Patent: May 28, 2019Assignee: United Technologies CorporationInventors: Joseph J. Czapski, Jr., David C. Pimenta, Chung-Han Liou, Paul R. Senofonte, Steven D. Roberts
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TURBINE CLEARANCE CONTROL SYSTEM AND METHOD FOR IMPROVED VARIABLE CYCLE GAS TURBINE ENGINE FUEL BURN
Publication number: 20190048796Abstract: A method of assembling a gas turbine engine includes setting a build clearance at assembly in response to a running tip clearance defined with a cooled cooling air. A method of operating a gas turbine engine includes supplying a cooled cooling air to a high pressure turbine in response to an engine rotor speed.Type: ApplicationFiled: July 30, 2018Publication date: February 14, 2019Applicant: United Technologies CorporationInventors: Walter A. Ledwith, Jr., Scott A. Carr, Christopher J. Hanlon, Peter A. White, Theodore W. Hall, John R. Farris, Andrew S. Miller, Christopher W. Robak, David C. Pimenta, David Richard Griffin -
TURBINE CLEARANCE CONTROL SYSTEM AND METHOD FOR IMPROVED VARIABLE CYCLE GAS TURBINE ENGINE FUEL BURN
Publication number: 20170328231Abstract: A method of assembling a gas turbine engine includes setting a build clearance at assembly in response to a running tip clearance defined with a cooled cooling air. A method of operating a gas turbine engine includes supplying a cooled cooling air to a high pressure turbine in response to an engine rotor speed.Type: ApplicationFiled: March 6, 2015Publication date: November 16, 2017Inventors: Walter A. Ledwith, JR., Scott A. Carr, Christopher J. Hanlon, Peter A. White, Theodore W. Hall, John R. Farris, Andrew S. Miller, Christopher W. Robak, David C. Pimenta, David Richard Griffin -
Publication number: 20170298867Abstract: Tracks (35), fastened to static structure of an aircraft engine nozzle, guide sliders (32) journaled in struts (27, 28) fastened to a flap (23) of the nozzle. Each slider and attached journal axle or bolt (33) is formed of cobalt, and each track slider surface (61) and journal bushings (43, 44) are formed of a nickel alloy to reduce wear from rubbing. Track slides (40, 41) are mounted to the static structure of the nozzle by blind bolts (68) having a tool recess (70) at its threaded tip to prevent the bolt (68) from turning as a nut is secured. Each slider has limited rotation due to a pin (102), thereon engaging a slot in a tab (100) of the bushing (43) to assist in inserting the slider (32) into the beveled ends of the tracks (35, 36), when mounting or replacing a flap.Type: ApplicationFiled: December 9, 2016Publication date: October 19, 2017Applicant: United Technologies CorporationInventors: Joseph J. Czapski, Jr., David C. Pimenta, Chung-Han Liou, Paul R. Senofonte, Steven D. Roberts
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Patent number: 9551294Abstract: Tracks (35), fastened to static structure of an aircraft engine nozzle, guide sliders (32) journaled in struts (27, 28) fastened to a flap (23) of the nozzle. Each slider and attached journal axle or bolt (33) is formed of cobalt, and each track slider surface (61) and journal bushings (43, 44) are formed of a nickel alloy to reduce wear from rubbing. Track slides (40, 41) are mounted to the static structure of the nozzle by blind bolts (68) having a tool recess (70) at its threaded tip to prevent the bolt (68) from turning as a nut is secured. Each slider has limited rotation due to a pin (102), thereon engaging a slot in a tab (100) of the bushing (43) to assist in inserting the slider (32) into the beveled ends of the tracks (35, 36), when mounting or replacing a flap.Type: GrantFiled: January 15, 2014Date of Patent: January 24, 2017Assignee: United Technologies CorporationInventors: Joseph J Czapski, Jr., David C Pimenta, Chung-Han Liou, Paul R Senofonte, Steven D. Roberts
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Publication number: 20160341075Abstract: A gas turbine engine includes a core assembly with a core case having a containment section for containing liberated compressor and turbine blades and blade fragments. The containment section includes first and second containment layers and the containment section is configured to have a non-linear rate of energy dissipation across the first and second containment layers, thereby to improve containment of blades and blade fragments.Type: ApplicationFiled: August 15, 2014Publication date: November 24, 2016Inventors: Shu Liu, Robert Russell Mayer, Paul W. Palmer, Peter Balawajder, Igor S. Garcia, David C. Pimenta, Stephanie Ernst, Fernando K. Grant, Eric Baker, Andrew S. Miller
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Patent number: 9228533Abstract: A gas turbine engine system includes an airframe support, a gas turbine engine mounted to the airframe support, a nozzle exhaust mounted to the airframe support, and a flexible annular seal having a first end that is attached to the gas turbine engine and a second end that is attached to an exhaust nozzle. The flexible annular seal may include a flexible annular wall that permits relative deflection between the gas turbine engine and the exhaust nozzle to facilitate the reduction of undesirable load transfer.Type: GrantFiled: November 30, 2007Date of Patent: January 5, 2016Assignee: United Technologies CorporationInventors: Steven D. Roberts, Richard W. Monahan, David C. Pimenta
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Publication number: 20150192092Abstract: Tracks (35), fastened to static structure of an aircraft engine nozzle, guide sliders (32) journaled in struts (27, 28) fastened to a flap (23) of the nozzle. Each slider and attached journal axle or bolt (33) is formed of cobalt, and each track slider surface (61) and journal bushings (43, 44) are formed of a nickel alloy to reduce wear from rubbing. Track slides (40, 41) are mounted to the static structure of the nozzle by blind bolts (68) having a tool recess (70) at its threaded tip to prevent the bolt (68) from turning as a nut is secured. Each slider has limited rotation due to a pin (102), thereon engaging a slot in a tab (100) of the bushing (43) to assist in inserting the slider (32) into the beveled ends of the tracks (35, 36), when mounting or replacing a flap.Type: ApplicationFiled: January 15, 2014Publication date: July 9, 2015Applicant: United Technologies CorporationInventors: Joseph J. Czapski, JR., David C. Pimenta, Chung-Han Liou, Paul R. Senofonte, Steven D. Roberts
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Patent number: 8647048Abstract: A system includes a gas turbine engine, a nozzle structure located adjacent to the gas turbine engine, a flexible annular seal linking the gas turbine engine and the nozzle structure, the flexible annular seal having a plurality of corrugate sections, and a reinforcement member positioned between two of the plurality of corrugate sections.Type: GrantFiled: June 30, 2011Date of Patent: February 11, 2014Assignee: United Technologies CorporationInventors: Steven D. Roberts, Richard W. Monahan, David C. Pimenta
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Patent number: 8459936Abstract: A system includes a gas turbine engine, a nozzle structure located adjacent to the gas turbine engine, a flexible annular seal linking the gas turbine engine and the nozzle structure, the flexible annular seal having a plurality of corrugate sections arranged about a centerline, and a connection device secured to the gas turbine engine and to the nozzle structure. The connection device is adjustable to select a length of the flexible annular seal measured along the centerline.Type: GrantFiled: June 30, 2011Date of Patent: June 11, 2013Assignee: United Technologies CorporationInventors: Jocelyn Charis Damgaard, Steven D. Roberts, Timothy Dale, Richard W. Monahan, David C. Pimenta
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Publication number: 20120131929Abstract: A system includes a gas turbine engine, a nozzle structure located adjacent to the gas turbine engine, a flexible annular seal linking the gas turbine engine and the nozzle structure, the flexible annular seal having a plurality of corrugate sections, and a reinforcement member positioned between two of the plurality of corrugate sections.Type: ApplicationFiled: June 30, 2011Publication date: May 31, 2012Applicant: UNITED TECHNOLOGIES CORPORATIONInventors: Steven D. Roberts, Richard W. Monahan, David C. Pimenta
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Publication number: 20120131928Abstract: A system includes a gas turbine engine, a nozzle structure located adjacent to the gas turbine engine, a flexible annular seal linking the gas turbine engine and the nozzle structure, the flexible annular seal having a plurality of corrugate sections arranged about a centerline, and a connection device secured to the gas turbine engine and to the nozzle structure. The connection device is adjustable to select a length of the flexible annular seal measured along the centerline.Type: ApplicationFiled: June 30, 2011Publication date: May 31, 2012Applicant: UNITED TECHNOLOGIES CORPORATIONInventors: Jocelyn Charis Damgaard, Steven D. Roberts, Timothy Dale, Richard W. Monahan, David C. Pimenta
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Publication number: 20090140497Abstract: A gas turbine engine system includes an airframe support, a gas turbine engine mounted to the airframe support, a nozzle exhaust mounted to the airframe support, and a flexible annular seal having a first end that is attached to the gas turbine engine and a second end that is attached to an exhaust nozzle. The flexible annular seal may include a flexible annular wall that permits relative deflection between the gas turbine engine and the exhaust nozzle to facilitate the reduction of undesirable load transfer.Type: ApplicationFiled: November 30, 2007Publication date: June 4, 2009Inventors: Steven D. Roberts, Richard W. Monahan, David C. Pimenta