Patents by Inventor Ronald Dutton
Ronald Dutton 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: 11353038Abstract: The gas turbine compressor for an aircraft gas turbine engine includes a compressor rotor having a plurality of compressor blades circumferentially distributed around a hub. Each of the compressor blades has an airfoil extending radially outward from the hub to a blade tip. A circumferential row of the compressor blades includes two or more different blade types, at least one modified blade of the two or more different blade types having means for generating different shock patterns between adjacent ones of the two or more different blade types when the gas turbine compressor operates in supersonic flow regimes. The means for generating different shock patterns on the modified blade aerodynamically mistune the two or more different blade types.Type: GrantFiled: April 29, 2020Date of Patent: June 7, 2022Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Ignatius Theratil, Krishna Prasad Balike, Aldo Abate, Sean Kelly, Peter Townsend, Ronald Dutton, Anthony Brown, Paul Stone, Myron Klein, Milica Kojovic, Robert Venditti
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Publication number: 20200392968Abstract: The gas turbine compressor for an aircraft gas turbine engine includes a compressor rotor having a plurality of compressor blades circumferentially distributed around a hub. Each of the compressor blades has an airfoil extending radially outward from the hub to a blade tip. A circumferential row of the compressor blades includes two or more different blade types, at least one modified blade of the two or more different blade types having means for generating different shock patterns between adjacent ones of the two or more different blade types when the gas turbine compressor operates in supersonic flow regimes. The means for generating different shock patterns on the modified blade aerodynamically mistune the two or more different blade types.Type: ApplicationFiled: April 29, 2020Publication date: December 17, 2020Inventors: Ignatius THERATIL, Krishna Prasad BALIKE, Aldo ABATE, Sean KELLY, Peter TOWNSEND, Ronald DUTTON, Anthony BROWN, Paul STONE, Myron KLEIN, Milica KOJOVIC, Robert VENDITTI
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Patent number: 10865807Abstract: A compressor rotor for a gas turbine engine is described which includes sets of blades having different airfoil thickness distributions, each including a frequency modifier forming a thickness differential relative to a baseline blade thickness. The frequency modifiers provide different natural vibration frequencies for each of the blades, and facilitate modifying natural vibration frequency separation between adjacent blades of the compressor rotor.Type: GrantFiled: January 11, 2019Date of Patent: December 15, 2020Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Ignatius Theratil, Krishna Prasad Balike, Sean Michael Kelly, Richard Ivakitch, Peter Townsend, Ronald Dutton, Paul Stone, Robert Venditti, Daniel Fudge, Milica Kojovic, Aldo Abate
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Patent number: 10808556Abstract: A strut and IGV configuration in a gas turbine engine positioned at an upstream of a rotor includes a plurality of radial struts, for example for bearing engine loads, and a plurality of inlet guide vanes positioned axially spaced apart from the struts. The number of inlet guide vanes is greater than the number of struts. The struts are circumferentially aligned with the inlet guide vanes.Type: GrantFiled: September 5, 2018Date of Patent: October 20, 2020Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Hong Yu, Ronald Dutton
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Patent number: 10724540Abstract: A turbofan engine is disclosed having a bypass duct with an asymmetry in aerodynamic profile caused by a local obstruction in the bypass duct. The engine comprises stator vanes circumferentially spaced-apart around a circumference of the bypass duct. A first group of adjacent stator vanes includes a majority of the plurality of stator vanes and are arranged in a first circumferential sector of the bypass duct and have equal stagger angles. A second group of adjacent stator vanes includes a minority of the plurality of stator vanes and are arranged in a second circumferential sector circumferentially positioned relative to the local obstruction. The stator vanes of the second group have stagger angles different from the stagger angles of the stator vanes of the first group.Type: GrantFiled: December 6, 2016Date of Patent: July 28, 2020Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Yau-Wai Li, Peter Townsend, Ronald Dutton, Bernadette Mason
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Patent number: 10670041Abstract: A compressor rotor, such as a fan, for a gas turbine engine is described which includes alternating at least first and second blade types. The leading edge of the second blade types includes a leading edge tip cutback extending to the blade tip thereof. The leading edge tip cutback of the second blade type defines a chord length at the blade tip of the second blade types that is less than that of the first blades types. The first and second blade types generate different shock patterns when the fan or compressor rotor operates in supersonic flow regimes.Type: GrantFiled: February 17, 2017Date of Patent: June 2, 2020Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Ignatius Theratil, Krishna Prasad Balike, Aldo Abate, Sean Kelly, Peter Townsend, Ronald Dutton, Anthony Brown, Paul Stone, Myron Klein, Milica Kojovic, Robert Venditti
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Publication number: 20200024954Abstract: A strut and IGV configuration in a gas turbine engine positioned at an upstream of a rotor includes a plurality of radial struts, for example for bearing engine loads, and a plurality of inlet guide vanes positioned axially spaced apart from the struts. The number of inlet guide vanes is greater than the number of struts. The struts are circumferentially aligned with the inlet guide vanes.Type: ApplicationFiled: September 5, 2018Publication date: January 23, 2020Inventors: Hong YU, Ronald DUTTON
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Publication number: 20190145431Abstract: A compressor rotor for a gas turbine engine is described which includes sets of blades having different airfoil thickness distributions, each including a frequency modifier forming a thickness differential relative to a baseline blade thickness. The frequency modifiers provide different natural vibration frequencies for each of the blades, and facilitate modifying natural vibration frequency separation between adjacent blades of the compressor rotor.Type: ApplicationFiled: January 11, 2019Publication date: May 16, 2019Inventors: Ignatius THERATIL, Krishna Prasad BALIKE, Sean Michael KELLY, Richard IVAKITCH, Peter TOWNSEND, Ronald DUTTON, Paul STONE, Robert VENDITTI, Daniel FUDGE, Milica KOJOVIC, Aldo ABATE
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Patent number: 10215194Abstract: A compressor rotor for a gas turbine engine is described which includes sets of blades having different airfoil thickness distributions, each including a frequency modifier forming a thickness differential relative to a baseline blade thickness. The frequency modifiers provide different natural vibration frequencies for each of the blades, and facilitate modifying natural vibration frequency separation between adjacent blades of the compressor rotor.Type: GrantFiled: December 21, 2015Date of Patent: February 26, 2019Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Ignatius Theratil, Krishna Prasad Balike, Richard Ivakitch, Sean Michael Kelly, Peter Townsend, Ronald Dutton, Paul Stone, Robert Venditti, Daniel Fudge, Milica Kojovic, Aldo Abate
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Patent number: 10094223Abstract: A strut and IGV configuration in a gas turbine engine positioned at an upstream of a rotor includes a plurality of radial struts, for example for bearing engine loads, and a plurality of inlet guide vanes positioned axially spaced apart from the struts. The number of inlet guide vanes is greater than the number of struts. The struts are circumferentially aligned with the inlet guide vanes.Type: GrantFiled: March 13, 2014Date of Patent: October 9, 2018Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Hong Yu, Ronald Dutton
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Publication number: 20180156235Abstract: A turbofan engine is disclosed having a bypass duct with an asymmetry in aerodynamic profile caused by a local obstruction in the bypass duct. The engine comprises stator vanes circumferentially spaced-apart around a circumference of the bypass duct. A first group of adjacent stator vanes includes a majority of the plurality of stator vanes and are arranged in a first circumferential sector of the bypass duct and have equal stagger angles. A second group of adjacent stator vanes includes a minority of the plurality of stator vanes and are arranged in a second circumferential sector circumferentially positioned relative to the local obstruction. The stator vanes of the second group have stagger angles different from the stagger angles of the stator vanes of the first group.Type: ApplicationFiled: December 6, 2016Publication date: June 7, 2018Inventors: Yau-Wai LI, Peter TOWNSEND, Ronald DUTTON, Bernadette MASON
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Patent number: 9759230Abstract: A multi-stage axial compressor with an inner wall including a step portion for each of the compressor stages. Each step portion is defined along a respective stage. Each step portion may extend over at least a majority of an axial length of the stage. Each step portion may optionally include a point aligned with a maximum thickness of the airfoil portions of the rotor blades and a point aligned with a maximum thickness of the stator vanes. Adjacent step portions are connected by a transition portion converging toward a central axis of the compressor from the upstream step to the downstream step. Each transition portion has a steeper slope than that of the adjacent step portions. A method of directing flow through a multi-stage axial flow compressor is also discussed.Type: GrantFiled: January 24, 2014Date of Patent: September 12, 2017Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Kari Heikurinen, Ronald Dutton
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Publication number: 20170241432Abstract: A compressor rotor, such as a fan, for a gas turbine engine is described which includes alternating at least first and second blade types. The leading edge of the second blade types includes a leading edge tip cutback extending to the blade tip thereof. The leading edge tip cutback of the second blade type defines a chord length at the blade tip of the second blade types that is less than that of the first blades types. The first and second blade types generate different shock patterns when the fan or compressor rotor operates in supersonic flow regimes.Type: ApplicationFiled: February 17, 2017Publication date: August 24, 2017Inventors: Ignatius THERATIL, Krishna Prasad BALIKE, Aldo ABATE, Sean KELLY, Peter TOWNSEND, Ronald DUTTON, Anthony BROWN, Paul STONE, Myron KLEIN, Milica KOJOVIC, Robert VENDITTI
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Publication number: 20170175776Abstract: A compressor rotor for a gas turbine engine is described which includes sets of blades having different airfoil thickness distributions, each including a frequency modifier forming a thickness differential relative to a baseline blade thickness. The frequency modifiers provide different natural vibration frequencies for each of the blades, and facilitate modifying natural vibration frequency separation between adjacent blades of the compressor rotor.Type: ApplicationFiled: December 21, 2015Publication date: June 22, 2017Inventors: Ignatius Theratil, Krishna Prasad Balike, Richard Ivakitch, Sean Michael Kelly, Peter Townsend, Ronald Dutton, Paul Stone, Robert Venditti, Daniel Fudge, Milica Kojovic, Aldo Abate
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Publication number: 20150260103Abstract: A strut and IGV configuration in a gas turbine engine positioned at an upstream of a rotor includes a plurality of radial struts, for example for bearing engine loads, and a plurality of inlet guide vanes positioned axially spaced apart from the struts. The number of inlet guide vanes is greater than the number of struts. The struts are circumferentially aligned with the inlet guide vanes.Type: ApplicationFiled: March 13, 2014Publication date: September 17, 2015Applicant: PRATT & WHITNEY CANADA CORP.Inventors: Hong YU, Ronald DUTTON
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Publication number: 20150211546Abstract: A multi-stage axial compressor with an inner wall including a step portion for each of the compressor stages. Each step portion is defined along a respective stage. Each step portion may extend over at least a majority of an axial length of the stage. Each step portion may optionally include a point aligned with a maximum thickness of the airfoil portions of the rotor blades and a point aligned with a maximum thickness of the stator vanes. Adjacent step portions are connected by a transition portion converging toward a central axis of the compressor from the upstream step to the downstream step. Each transition portion has a steeper slope than that of the adjacent step portions. A method of directing flow through a multi-stage axial flow compressor is also discussed.Type: ApplicationFiled: January 24, 2014Publication date: July 30, 2015Applicant: Pratt & Whitney Canada Corp.Inventors: Kari HEIKURINEN, Ronald DUTTON
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Publication number: 20050254956Abstract: A method for reducing vortex promotion of a rotor blade used in high core PR fans comprises shifting a curvature distribution of a blade section immediately adjacent to the hub such that a major turning of the suction side of the section is located near a trailing edge of the blade.Type: ApplicationFiled: May 14, 2004Publication date: November 17, 2005Inventors: Ronald Dutton, Kimberley MacDonald