Patents by Inventor John H. Mosley
John H. Mosley 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: 11939919Abstract: A fluid supply system for a gas turbine engine includes a first component and a second component. A fluid fitting has a fluid junction. The fluid junction includes a first fluid port in fluid communication with and configured to supply a first cooling fluid to the first component. The fluid junction includes a second fluid port in fluid communication with and configured to supply a second cooling fluid to the second component. A primary pipe is fluidly connected to the fluid fitting. A flow meter is arranged upstream from the fluid junction and is configured to receive a cooling supply fluid from a fluid source. Thee flow meter is a wall having an orifice and a surface that is radiused and convex facing into the cooling supply fluid. A secondary pipe is secured to the fluid fitting and is configured to supply the second cooling fluid to the second component. A turbine section includes the first and second components.Type: GrantFiled: June 12, 2019Date of Patent: March 26, 2024Assignee: RTX CorporationInventors: John H. Mosley, Michelle Diana Stearns, Michael Luther Comeau, James P. Chasse
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Patent number: 11578668Abstract: A gas turbine engine includes a compressor section, a combustor, and a turbine section. The turbine section includes a high pressure turbine comprising a plurality of turbine blades. The gas turbine engine includes a tap for tapping air that is compressed by the compressor, to be passed through a heat exchanger to cool the air, the cooled air to be passed to the plurality of turbine blades. A sensor is located downstream of a leading edge of the combustor, and is configured to measure a characteristic of the cooled air. A controller is configured to compare the measured characteristic to a threshold and control an operating condition of the gas turbine engine based on the comparison.Type: GrantFiled: May 30, 2017Date of Patent: February 14, 2023Assignee: Raytheon Technologies CorporationInventors: Jonathan Ortiz, Taryn Narrow, John H. Mosley, Zachary Mott, Paul R. Hanrahan
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Publication number: 20210317785Abstract: A cooling system includes an inlet, a passageway, and a feed passage. The inlet is defined by a strut of a diffuser case that extends between a first case portion and a second case portion. The inlet extends from a leading surface towards a trailing surface along a first axis. The passageway is defined by the strut and extends from the inlet towards the second case portion along a second axis that is disposed transverse to the first axis. The feed passage is defined between a body of a tangential onboard injection system that extends between and is connected to an inner vane platform of a guide vane and the second case portion. The feed passage extends along an axis that is disposed parallel to the first axis.Type: ApplicationFiled: April 9, 2020Publication date: October 14, 2021Inventors: Enzo DiBenedetto, Anthony R. Bifulco, William K. Ackermann, Paul E. Coderre, John H. Mosley, Stephen K. Kramer
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Patent number: 10815891Abstract: An inner diffuser case for use in a combustor of a gas turbine engine includes a multiple of struts across an annular flow path between an outer shroud and an inner shroud, at least one of the multiple of struts is an open strut.Type: GrantFiled: September 27, 2013Date of Patent: October 27, 2020Assignee: Raytheon Technologies CorporationInventors: Chris J. Niggemeier, Karl D. Blume, John H. Mosley, Andreas Sadil
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Publication number: 20200032711Abstract: A fluid supply system for a gas turbine engine includes a first component and a second component. A fluid fitting has a fluid junction. The fluid junction includes a first fluid port in fluid communication with and configured to supply a first cooling fluid to the first component. The fluid junction includes a second fluid port in fluid communication with and configured to supply a second cooling fluid to the second component. A primary pipe is fluidly connected to the fluid fitting. A flow meter is arranged upstream from the fluid junction and is configured to receive a cooling supply fluid from a fluid source. Thee flow meter is a wall having an orifice and a surface that is radiused and convex facing into the cooling supply fluid. A secondary pipe is secured to the fluid fitting and is configured to supply the second cooling fluid to the second component. A turbine section includes the first and second components.Type: ApplicationFiled: June 12, 2019Publication date: January 30, 2020Inventors: John H. Mosley, Michelle Diana Stearns, Michael Luther Comeau, James P. Chasse
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Patent number: 10443498Abstract: A cooling fluid system for a gas turbine engine includes a fluid source. A turbine section includes first and second components. A fluid supply system has a primary pipe that is configured to provide a cooling supply fluid from the fluid source to a fluid fitting having a fluid junction. The fluid junction is in fluid communication with and is configured to supply a first cooling fluid to the first component. The fluid junction is in fluid communication with and is configured to supply a second cooling fluid to the second component. A flow meter is upstream from the fluid junction and is configured to receive the cooling supply fluid.Type: GrantFiled: August 5, 2015Date of Patent: October 15, 2019Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: John H. Mosley, Michelle Diana Stearns, Michael Luther Comeau, James P. Chasse
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Patent number: 10215098Abstract: A sealing arrangement includes a turbine static structure with a seal ring having groove with a contact surface. Also included is a bearing compartment with a second contact surface, and a piston seal positioned between the turbine static structure and the bearing compartment. The piston seal includes sides configured to contact the contact surfaces and is positioned in the groove.Type: GrantFiled: January 22, 2015Date of Patent: February 26, 2019Assignee: United Technologies CorporationInventors: Anthony P. Cherolis, Jorge I. Farah, Seth A. Max, John H. Mosley, Steven D. Porter, Gregory E. Reinhardt, Kevin Zacchera
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Publication number: 20180347472Abstract: A gas turbine engine includes a compressor section, a combustor, and a turbine section. The turbine section includes a high pressure turbine comprising a plurality of turbine blades. The gas turbine engine includes a tap for tapping air that is compressed by the compressor, to be passed through a heat exchanger to cool the air, the cooled air to be passed to the plurality of turbine blades. A sensor is located downstream of a leading edge of the combustor, and is configured to measure a characteristic of the cooled air. A controller is configured to compare the measured characteristic to a threshold and control an operating condition of the gas turbine engine based on the comparison.Type: ApplicationFiled: May 30, 2017Publication date: December 6, 2018Inventors: Jonathan Ortiz, Taryn Narrow, John H. Mosley, Zachary Mott, Paul R. Hanrahan
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Patent number: 10072585Abstract: A cooling system for a gas turbine engine turbine section includes a rotor supporting a blade having a cooling passage. A disc is secured relative to the rotor and it forms a cavity between the rotor and the disc. A bleed air source is in fluid communication with the cavity. An impeller is arranged in the cavity. The impeller is configured to increase a fluid pressure within the cavity to drive bleed air from the bleed air source and thereby provide a pressurized cooling fluid to the cooling passage.Type: GrantFiled: March 10, 2014Date of Patent: September 11, 2018Assignee: United Technologies CorporationInventors: John H. Mosley, James P. Chrisikos, John J. O'Connor, Charles C. Wu, David Glasspoole, Roger Gates
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Patent number: 9995171Abstract: A mid-turbine frame for a gas turbine engine includes an outer frame case and an inner frame case. At least one spoke connects the outer frame case to the inner frame case. The spoke includes an inlet passage with at least one branch that extends in an axial direction.Type: GrantFiled: January 16, 2015Date of Patent: June 12, 2018Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Andrew D. Burdick, Anthony P. Cherolis, Christopher Treat, Jonathan Lemoine, Robert Russell Mayer, Jorge I. Farah, John H. Mosley
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Patent number: 9920651Abstract: A mid-turbine frame for a gas turbine engine includes an inner frame case that includes a fluid passage. At least one spoke includes an inlet passage with at least one branch extending in an axial direction in fluid communication with the fluid passage in the inner frame case. A fitting fluidly connects the at least one branch to the fluid passage in the inner frame case. The fitting also includes a transfer tube connecting the cooling airflow passage to a cup boss. The transfer tube is fixed relative to the cylindrical portion and moveable relative to the cup boss. A swirler tube is in fluid communication with the fluid passage and is configured to direct cooling airflow in a radial inward and downstream direction.Type: GrantFiled: January 16, 2015Date of Patent: March 20, 2018Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Anthony P. Cherolis, John H. Mosley, Kalpendu J. Parekh, Christopher Treat, Alberto A. Mateo
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Patent number: 9803502Abstract: A mid-turbine frame assembly includes an inner frame case which includes a first plurality of holes and a second plurality of holes. A plurality of tie rods is circumferentially spaced around the inner frame case and includes an inlet passage that is aligned with the first plurality of holes. A plurality of hollow airfoils is aligned with the second plurality of holes.Type: GrantFiled: February 9, 2015Date of Patent: October 31, 2017Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Anthony P. Cherolis, Jeffrey J. Lienau, Robert Newman, John H. Mosley, Joshua Daniel Winn, Paul K. Sanchez
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Publication number: 20160230598Abstract: A mid-turbine frame assembly includes an inner frame case which includes a first plurality of holes and a second plurality of holes. A plurality of tie rods is circumferentially spaced around the inner frame case and includes an inlet passage that is aligned with the first plurality of holes. A plurality of hollow airfoils is aligned with the second plurality of holes.Type: ApplicationFiled: February 9, 2015Publication date: August 11, 2016Inventors: Anthony P. Cherolis, Jeffrey J. Lienau, Robert Newman, John H. Mosley, Joshua Daniel Winn, Paul K. Sanchez
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Publication number: 20160215702Abstract: A sealing arrangement includes a turbine static structure with a seal ring having groove with a contact surface. Also included is a bearing compartment with a second contact surface, and a piston seal positioned between the turbine static structure and the bearing compartment. The piston seal includes sides configured to contact the contact surfaces and is positioned in the groove.Type: ApplicationFiled: January 22, 2015Publication date: July 28, 2016Inventors: Anthony P. Cherolis, Jorge I. Farah, Seth A. Max, John H. Mosley, Steven D. Porter, Gregory E. Reinhardt, Kevin Zacchera
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Publication number: 20160208647Abstract: A mid-turbine frame for a gas turbine engine includes an inner frame case that includes a fluid passage. A swirler tube is in fluid communication with the fluid passage and is configured to direct cooling airflow in a radial inward and downstream direction.Type: ApplicationFiled: January 16, 2015Publication date: July 21, 2016Inventors: Anthony P. Cherolis, John H. Mosley, Kalpendu J. Parekh, Christopher Treat, Alberto A. Mateo
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Publication number: 20160208644Abstract: A mid-turbine frame for a gas turbine engine includes an outer frame case and an inner frame case. At least one spoke connects the outer frame case to the inner frame case. The spoke includes an inlet passage with at least one branch that extends in an axial direction.Type: ApplicationFiled: January 16, 2015Publication date: July 21, 2016Inventors: Andrew D. Burdick, Anthony P. Cherolis, Christopher Treat, Jonathan Lemoine, Robert Russell Mayer, Jorge I. Farah, John H. Mosley
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Publication number: 20160047311Abstract: A cooling fluid system for a gas turbine engine includes a fluid source. A turbine section includes first and second components. A fluid supply system has a primary pipe that is configured to provide a cooling supply fluid from the fluid source to a fluid fitting having a fluid junction. The fluid junction is in fluid communication with and is configured to supply a first cooling fluid to the first component. The fluid junction is in fluid communication with and is configured to supply a second cooling fluid to the second component. A flow meter is upstream from the fluid junction and is configured to receive the cooling supply fluid.Type: ApplicationFiled: August 5, 2015Publication date: February 18, 2016Inventors: John H. Mosley, Michelle Diana Stearns, Michael Luther Comeau, James P. Chasse
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Publication number: 20160003166Abstract: A cooling system for a gas turbine engine turbine section includes a rotor supporting a blade having a cooling passage. A disc is secured relative to the rotor and it forms a cavity between the rotor and the disc. A bleed air source is in fluid communication with the cavity. An impeller is arranged in the cavity. The impeller is configured to increase a fluid pressure within the cavity to drive bleed air from the bleed air source and thereby provide a pressurized cooling fluid to the cooling passage.Type: ApplicationFiled: March 10, 2014Publication date: January 7, 2016Inventors: John H. Mosley, James P. Chrisikos, Roger Gates, John J. O'Connor, Charles C. Wu, David Glasspoole
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Publication number: 20150252729Abstract: An inner diffuser case for use in a combustor of a gas turbine engine includes a multiple of struts across an annular flow path between an outer shroud and an inner shroud, at least one of the multiple of struts is an open strut.Type: ApplicationFiled: September 27, 2013Publication date: September 10, 2015Inventors: Chris J. Niggemeier, Karl D. Blume, John H. Mosley, Andreas Sadil
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Patent number: 9091173Abstract: A gas turbine engine configured to rotate in a circumferential direction about an axis extending through a center of the gas turbine engine comprises a turbine stage. The turbine stage comprises a disk, a plurality of blades and a mini-disk. The disk comprises an outer diameter edge having slots, an inner diameter bore surrounding the axis, a forward face, and an aft face. The plurality of blades is coupled to the slots. The mini-disk is coupled to the aft face of the rotor to define a cooling plenum therebetween in order to direct cooling air to the slots. In one embodiment of the invention, the cooling plenum is connected to a radially inner compressor bleed air inlet through all rotating components so that cooling air passes against the inner diameter bore.Type: GrantFiled: May 31, 2012Date of Patent: July 28, 2015Assignee: United Technologies CorporationInventors: John H. Mosley, Ioannis Alvanos, Phililp S. Stripinis, Douglas Paul Freiberg, Hector M. Pinero, John J. O'Connor, Jon Pietrobon