Patents by Inventor Christopher M. Valva
Christopher M. Valva 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: 11946383Abstract: A gas turbine engine includes a first bearing compartment and a seal assembly within the first bearing compartment that includes a rotatable seal seat, a gutter radially outward of the seal seat and fixed against rotation. The gutter includes a channel on its radially inner face. A second bearing compartment is also included. A scavenge pump is in communication with a first supply line configured to supply the first bearing compartment and a second supply line configured to supply the second bearing compartment. The gutter is in communication with the scavenge pump through a gutter scavenge line.Type: GrantFiled: June 28, 2022Date of Patent: April 2, 2024Assignee: RTX CorporationInventors: Todd A. Davis, Christopher M. Valva
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Patent number: 11879396Abstract: A turbomachine has a bearing in a bearing compartment. A first seal system isolates the bearing compartment and has: a first runner; a second runner; an inner seal encircling the first runner; and an outer seal encircling the second runner. The inner seal has a static clearance with the first runner. The outer seal has a static clearance with the second runner, greater than the inner seal static clearance. The first runner has an inner portion cantilevered inward. The second runner has an outer portion cantilevered outward.Type: GrantFiled: November 22, 2022Date of Patent: January 23, 2024Assignee: RTX CorporationInventors: Michael A Beinor, Timothy J. Castaldo, Christopher M. Valva, Nasr A. Shuaib, Mitchell D. Panton
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Publication number: 20230399978Abstract: A gas turbine engine has a shaft having an inner diameter surface. A plug is mounted in the shaft. An oil nozzle is positioned to direct a flow of oil to an interior of the shaft. The plug has: a first section; a second section having an outer diameter periphery; and an axial gap between the first section and the second section.Type: ApplicationFiled: June 10, 2022Publication date: December 14, 2023Applicant: Raytheon Technologies CorporationInventors: Russell B. Witlicki, Todd A. Davis, Ryan William Lureau, Shadd Andrew Bradshaw, Christopher M. Valva
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Publication number: 20230304443Abstract: A turbomachine has a bearing in a bearing compartment. A first seal system isolates the bearing compartment and has: a first runner; a second runner; an inner seal encircling the first runner; and an outer seal encircling the second runner. The inner seal has a static clearance with the first runner. The outer seal has a static clearance with the second runner, greater than the inner seal static clearance. The first runner has an inner portion cantilevered inward. The second runner has an outer portion cantilevered outward.Type: ApplicationFiled: November 22, 2022Publication date: September 28, 2023Applicant: Raytheon Technologies CorporationInventors: Michael A. Beinor, Timothy J. Castaldo, Christopher M. Valva, Nasr A. Shuaib, Mitchell D. Panton
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Patent number: 11549444Abstract: A turbomachine has a bearing in a bearing compartment. A first seal system isolates the bearing compartment and has: a first runner; a second runner; an inner seal encircling the first runner; and an outer seal encircling the second runner. The inner seal has a static clearance with the first runner. The outer seal has a static clearance with the second runner, greater than the inner seal static clearance. The first runner has an inner portion cantilevered inward. The second runner has an outer portion cantilevered outward.Type: GrantFiled: February 5, 2021Date of Patent: January 10, 2023Assignee: Raytheon Technologies CorporationInventors: Michael A. Beinor, Timothy J. Castaldo, Christopher M. Valva, Nasr A. Shuaib, Mitchell D. Panton
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Publication number: 20220325633Abstract: A gas turbine engine includes a first bearing compartment and a seal assembly within the first bearing compartment that includes a rotatable seal seat, a gutter radially outward of the seal seat and fixed against rotation. The gutter includes a channel on its radially inner face. A second bearing compartment is also included. A scavenge pump is in communication with a first supply line configured to supply the first bearing compartment and a second supply line configured to supply the second bearing compartment. The gutter is in communication with the scavenge pump through a gutter scavenge line.Type: ApplicationFiled: June 28, 2022Publication date: October 13, 2022Inventors: Todd A. Davis, Christopher M. Valva
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Patent number: 11466588Abstract: A gas turbine engine component includes an inner support structure surrounding an engine center axis and fixed to an engine static structure, an outer support structure spaced radially outward of the inner support structure, and a curved beam comprised of a plurality of curved beam spring segments that are positioned adjacent to each other to form a ring. The inner and outer support structures are coupled together around the curved beam to enclose the curved beam therebetween and form an assembly. A bearing is spaced radially inward of the assembly.Type: GrantFiled: October 30, 2019Date of Patent: October 11, 2022Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: David C. Kiely, Todd A. Davis, Russell B. Witlicki, Christopher M. Valva, Andrew Newton
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Publication number: 20220252013Abstract: A turbomachine has a bearing in a bearing compartment. A first seal system isolates the bearing compartment and has: a first runner; a second runner; an inner seal encircling the first runner; and an outer seal encircling the second runner. The inner seal has a static clearance with the first runner. The outer seal has a static clearance with the second runner, greater than the inner seal static clearance. The first runner has an inner portion cantilevered inward. The second runner has an outer portion cantilevered outward.Type: ApplicationFiled: February 5, 2021Publication date: August 11, 2022Applicant: Raytheon Technologies CorporationInventors: Michael A. Beinor, Timothy J. Castaldo, Christopher M. Valva, Nasr A. Shuaib, Mitchell D. Panton
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Patent number: 11401833Abstract: A gas turbine engine includes a first bearing compartment and a seal assembly within the first bearing compartment that includes a rotatable seal seat, a gutter radially outward of the seal seat and fixed against rotation. The gutter includes a channel on its radially inner face. A second bearing compartment is also included. A scavenge pump is in communication with a first supply line configured to supply the first bearing compartment and a second supply line configured to supply the second bearing compartment. The gutter is in communication with the scavenge pump through a gutter scavenge line. A valve between the scavenge pump and the second supply line is configured to close in response to a dry port event, such that closing the valve stops oil supply to the second supply line, while allowing oil supply to the first supply line.Type: GrantFiled: December 10, 2018Date of Patent: August 2, 2022Assignee: Raytheon Technologies CorporationInventors: Todd A. Davis, Christopher M. Valva
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Patent number: 11118629Abstract: A gas turbine engine component includes a bearing configured to support a shaft for rotation about an axis, wherein the bearing includes an outer race and an inner race, and a bearing housing spaced radially outwardly of the outer race. A curved beam centering spring is positioned between the outer race and the bearing housing. A cylindrical wall is radially outward of the bearing housing and engages the outer race and the bearing housing.Type: GrantFiled: December 11, 2019Date of Patent: September 14, 2021Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Russell B. Witlicki, Todd A. Davis, Christopher M. Valva, David C. Kiely, Andrew Newton
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Patent number: 11092037Abstract: The present disclosure is applicable to all gear trains using a journal bearing as a means of supporting gear shaft rotation. It is related in some embodiments to a system and method for supplying lubricant to the journal bearings of a gear-turbofan engine gear train when the fan rotor is subjected to a wind-milling condition in both directions, either clockwise or counterclockwise.Type: GrantFiled: August 29, 2019Date of Patent: August 17, 2021Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Christopher M. Valva, Brian P. Cigal
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Publication number: 20210180651Abstract: A gas turbine engine component includes a bearing configured to support a shaft for rotation about an axis, wherein the bearing includes an outer race and an inner race, and a bearing housing spaced radially outwardly of the outer race. A curved beam centering spring is positioned between the outer race and the bearing housing. A cylindrical wall is radially outward of the bearing housing and engages the outer race and the bearing housing.Type: ApplicationFiled: December 11, 2019Publication date: June 17, 2021Inventors: Russell B. Witlicki, Todd A. Davis, Christopher M. Valva, David C. Kiely, Andrew Newton
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Patent number: 11035252Abstract: A gas turbine engine component includes a ring comprising a single-piece component having an outer peripheral surface and an inner peripheral surface that surrounds an engine center axis, a plurality of outer diameter pedestals formed in the outer peripheral surface and circumferentially spaced apart from each other, and a plurality of inner diameter pedestals formed in the inner peripheral surface and circumferentially spaced apart from each other. A plurality of recesses are formed in the outer peripheral surface and are circumferentially spaced apart from each other.Type: GrantFiled: October 30, 2019Date of Patent: June 15, 2021Assignee: Raytheon Technologies CorporationInventors: Todd A. Davis, Russell B. Witlicki, Christopher M. Valva, Andrew Newton, David C. Kiely
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Publication number: 20210131307Abstract: A gas turbine engine component includes a ring comprising a single-piece component having an outer peripheral surface and an inner peripheral surface that surrounds an engine center axis, a plurality of outer diameter pedestals formed in the outer peripheral surface and circumferentially spaced apart from each other, and a plurality of inner diameter pedestals formed in the inner peripheral surface and circumferentially spaced apart from each other. A plurality of recesses are formed in the outer peripheral surface and are circumferentially spaced apart from each other.Type: ApplicationFiled: October 30, 2019Publication date: May 6, 2021Inventors: Todd A. Davis, Russell B. Witlicki, Christopher M. Valva, Andrew Newton, David C. Kiely
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Publication number: 20210131304Abstract: A gas turbine engine component includes an inner support structure surrounding an engine center axis and fixed to an engine static structure, an outer support structure spaced radially outward of the inner support structure, and a curved beam comprised of a plurality of curved beam spring segments that are positioned adjacent to each other to form a ring. The inner and outer support structures are coupled together around the curved beam to enclose the curved beam therebetween and form an assembly. A bearing is spaced radially inward of the assembly.Type: ApplicationFiled: October 30, 2019Publication date: May 6, 2021Inventors: David C. Kiely, Todd A. Davis, Russell B. Witlicki, Christopher M. Valva, Andrew Newton
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Patent number: 10962060Abstract: A seal assembly for a bearing compartment of a gas turbine engine includes a seal carrier, a seal element, a seal plate, and a trough. At least a portion of the seal element is within the seal carrier. The seal plate is in contact with the seal element and is configured to rotate relative to the seal element. The trough extends around the seal plate and comprises an annular channel positioned to capture oil slung from the seal plate.Type: GrantFiled: April 16, 2020Date of Patent: March 30, 2021Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Christopher T. Anglin, Dwayne E. Messerschmidt, Christopher M. Valva, Todd M. Gaulin
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Patent number: 10830078Abstract: An assembly is provided for a turbine engine. This turbine engine assembly includes a tower shaft rotatable about an axis, an engine component rotatable with the tower shaft about the axis, and a seal assembly. The engine component extends axially along the axis to an end surface. The seal assembly includes a carbon seal element, where the carbon seal element circumscribes the tower shaft and axially engages the end surface.Type: GrantFiled: September 14, 2018Date of Patent: November 10, 2020Assignee: Raytheon Technologies CorporationInventors: Brad E. Fiore, James B. Coffin, Christopher M. Valva
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Patent number: 10767560Abstract: A bearing assembly for a gas turbine engine includes, among other things, a bearing housing extending along an axis to define a bearing compartment, a lubricant seal assembly adjacent to the bearing housing to bound the bearing compartment, an air seal assembly defining a vent cavity along the bearing housing, wherein a mixing cavity is defined between the lubricant seal assembly and the air seal assembly, and wherein the bearing housing defines an airflow supply passage, an airflow vent passage and a scupper passage having respective fluid ports at different circumferential positions relative to the axis, the fluid port of the airflow vent passage fluidly coupled to the vent cavity, and the fluid ports of the airflow supply and scupper passages fluidly coupled to the mixing cavity. A method of sealing for a gas turbine engine is also disclosed.Type: GrantFiled: September 11, 2018Date of Patent: September 8, 2020Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Daniel S. Rogers, Taryn Narrow, Gregory E. Reinhardt, Collin P. Fitzgerald, Christopher M. Valva, Leonard Kolshak
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Patent number: 10767867Abstract: A bearing support may include a central shaft, a flange shaft, and a tube boss. The central shaft may include a central longitudinal axis extending between a first end and a second end of the bearing support. The flange shaft may extend radially outward of the central shaft at an acute angle, relative to the central longitudinal axis from the first end to the second end, and the flange shaft may include a rim defining an aperture. The tube boss extends from the central shaft radially outward through the aperture, according to various embodiments. An annular channel may be between the rim and the tube boss.Type: GrantFiled: March 21, 2018Date of Patent: September 8, 2020Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Todd A. Davis, Christopher M. Valva, Daniel Rosen, Armando Amador, Aneil S. Hegde, Ramin M. Rafatpanah
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Publication number: 20200240471Abstract: A seal assembly for a bearing compartment of a gas turbine engine includes a seal carrier, a seal element, a seal plate, and a trough. At least a portion of the seal element is within the seal carrier. The seal plate is in contact with the seal element and is configured to rotate relative to the seal element. The trough extends around the seal plate and comprises an annular channel positioned to capture oil slung from the seal plate.Type: ApplicationFiled: April 16, 2020Publication date: July 30, 2020Inventors: Christopher T. Anglin, Dwayne E. Messerschmidt, Christopher M. Valva, Todd M. Gaulin