Patents by Inventor Kari Heikurinen
Kari Heikurinen 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: 11002293Abstract: A compressor rotor for a gas turbine engine includes a hub disposed about an axis of rotation and an outer surface forming a radially inner gaspath boundary, the outer surface defining a nominal hub diameter. A circumferential array of blades extends radially outwardly from the hub. A first inter-blade passage is defined between a first set of adjacent blades and has a first throat area. A second inter-blade passage is defined between a second set of adjacent blades and has a second throat area that is smaller than the first throat area. At least one scoop is disposed in the second inter-blade passage, the scoop defining a cavity extending radially into the outer surface of the hub relative to the nominal hub diameter.Type: GrantFiled: September 15, 2017Date of Patent: May 11, 2021Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Karan Anand, Farid Abrari, Ernest Adique, Paul Aitchison, Daniel Fudge, Kari Heikurinen, Paul Stone, Tibor Urac, Thomas Veitch
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Patent number: 10865806Abstract: A rotor for a gas turbine engine. The rotor includes blades circumferentially distributed around a hub. The blades have airfoils with a span defined between a root and tip, a chord defined between a leading edge and a trailing edge, and a thickness defined between a pressure side surface and suction side surface. The blades include first blades and second blades. The airfoil of the first blades has a first thickness distribution defining a first natural vibration frequency of the airfoils of the first blades. The airfoil of the second blades has a second thickness distribution defining a second natural vibration frequency different than the first natural vibration frequency. The first thickness distribution is different than the second thickness distribution along a radially-inner half of the span, and the first thickness distribution matches the second thickness distribution along a radially-outer half of the span.Type: GrantFiled: September 15, 2017Date of Patent: December 15, 2020Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Thomas Veitch, Farid Abrari, Ernest Adique, Daniel Fudge, Kari Heikurinen, Paul Stone, Ignatius Theratil, Peter Townsend, Tibor Urac
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Patent number: 10837459Abstract: A fan for a gas turbine engine comprises blades distributed around a hub. The blades include first and second blades, having geometric parameters and/or material properties that differ from each other to frequency mistune the fan. The blades are distributed about the hub with at least one second blade between adjacent first blades. The leading edge of the airfoil of the second blades is disposed axially aft of the corresponding leading edge of the first blades in at least a portion of the blade span.Type: GrantFiled: October 6, 2017Date of Patent: November 17, 2020Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Thomas Veitch, Farid Abrari, Ernest Adique, Daniel Fudge, Kari Heikurinen, Paul Stone, Ignatius Theratil, Peter Townsend, Tibor Urac
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Patent number: 10689987Abstract: A compressor rotor for a gas turbine engine has blades circumferentially distributed around and extending a span length from a central hub. The blades include alternating first and second blades having airfoils with corresponding geometric profiles. The airfoil of the first blade has a coating varying in thickness relative to the second blade to provide natural vibration frequencies different between the first and the second blades.Type: GrantFiled: September 6, 2019Date of Patent: June 23, 2020Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Thomas Veitch, Farid Abrari, Ernest Adique, Paul Aitchison, Daniel Fudge, Kari Heikurinen, Paul Stone, Tibor Urac
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Publication number: 20200018176Abstract: A compressor rotor for a gas turbine engine has blades circumferentially distributed around and extending a span length from a central hub. The blades include alternating first and second blades having airfoils with corresponding geometric profiles. The airfoil of the first blade has a coating varying in thickness relative to the second blade to provide natural vibration frequencies different between the first and the second blades.Type: ApplicationFiled: September 6, 2019Publication date: January 16, 2020Inventors: Thomas VEITCH, Farid ABRARI, Ernest ADIQUE, Paul AITCHISON, Daniel FUDGE, Kari HEIKURINEN, Paul STONE, Tibor URAC
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Patent number: 10443411Abstract: A compressor rotor for a gas turbine engine has blades circumferentially distributed around and extending a span length from a central hub. The blades include alternating first and second blades having airfoils with corresponding geometric profiles. The airfoil of the first blade has a coating varying in thickness relative to the second blade to provide natural vibration frequencies different between the first and the second blades.Type: GrantFiled: September 18, 2017Date of Patent: October 15, 2019Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Thomas Veitch, Farid Abrari, Ernest Adique, Paul Aitchison, Daniel Fudge, Kari Heikurinen, Paul Stone, Tibor Urac
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Patent number: 10408223Abstract: A fan for a turbofan gas turbine engine having a low hub-to-tip ratio is disclosed. The fan includes a rotor hub and a plurality of radially extending fan blades. Each fan blade defines a hub radius (RHUB), which is the radius of the leading edge at the hub relative to a centerline of the fan, and a tip radius (RTIP), which is the radius of the leading edge at a tip of the fan blade relative to the centerline of the fan. The ratio of the hub radius to the tip radius (RHUB/RTIP) is less than 0.29. In a particular embodiment, this ratio is between 0.25 and 0.29. In another particular embodiment, this ratio is less than 0.25.Type: GrantFiled: June 7, 2017Date of Patent: September 10, 2019Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Kari Heikurinen, Peter Townsend
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Patent number: 10408231Abstract: A rotor for a gas turbine engine comprises a rotor having a hub and blades around the hub, and extending from the hub to tips. The tips include first and second tip portions between their respective tip leading edge and tip trailing edge. Tips are spaced from a rotational axis of the rotor by spans. A mean span of a first tip portion of a first blade is greater than a mean span of a corresponding first tip portion of a second blade. A mean span of a second tip portion the first blade is less than a mean span of a corresponding second tip portion of the second blade.Type: GrantFiled: September 13, 2017Date of Patent: September 10, 2019Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Thomas Veitch, Farid Abrari, Ernest Adique, Daniel Fudge, Kari Heikurinen, Paul Stone, Ignatius Theratil, Peter Townsend, Tibor Urac
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Patent number: 10370973Abstract: A compressor airfoil of a gas turbine engine includes a pressure side and a suction side of the airfoil extending downstream from a stagnation point, the suction side including a suction side surface portion within a leading edge region, and a main suction side airfoil surface downstream from the suction side surface portion and extending contiguously therewith. The suction side surface portion having a compound curvature profile which includes at least a leading edge having a first curvature profile and a chamfered surface having a second curvature profile different from the first curvature profile. The chamfered surface being contiguous with and extending immediately downstream from the leading edge. The first curvature profile being curved. The second curvature profile of the chamfered surface being substantially flat and defining a substantially straight-line profile in a cross-section transverse to the span-wise axis of the airfoil.Type: GrantFiled: May 29, 2015Date of Patent: August 6, 2019Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Kari Heikurinen, Ron Dutton
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Publication number: 20190107123Abstract: A fan for a gas turbine engine comprises blades distributed around a hub. The blades include first and second blades, having geometric parameters and/or material properties that differ from each other to frequency mistune the fan. The blades are distributed about the hub with at least one second blade between adjacent first blades. The leading edge of the airfoil of the second blades is disposed axially aft of the corresponding leading edge of the first blades in at least a portion of the blade span.Type: ApplicationFiled: October 6, 2017Publication date: April 11, 2019Inventors: Thomas VEITCH, Farid ABRARI, Ernest ADIQUE, Daniel FUDGE, Kari HEIKURINEN, Paul STONE, Ignatius THERATIL, Peter TOWNSEND, Tibor URAC
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Publication number: 20190085708Abstract: A compressor rotor for a gas turbine engine has blades circumferentially distributed around and extending a span length from a central hub. The blades include alternating first and second blades having airfoils with corresponding geometric profiles. The airfoil of the first blade has a coating varying in thickness relative to the second blade to provide natural vibration frequencies different between the first and the second blades.Type: ApplicationFiled: September 18, 2017Publication date: March 21, 2019Inventors: Thomas VEITCH, Farid ABRARI, Ernest ADIQUE, Paul AITCHISON, Daniel FUDGE, Kari HEIKURINEN, Paul STONE, Tibor URAC
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Publication number: 20190085868Abstract: A compressor rotor for a gas turbine engine includes a hub disposed about an axis of rotation and an outer surface forming a radially inner gaspath boundary, the outer surface defining a nominal hub diameter. A circumferential array of blades extends radially outwardly from the hub. A first inter-blade passage is defined between a first set of adjacent blades and has a first throat area. A second inter-blade passage is defined between a second set of adjacent blades and has a second throat area that is smaller than the first throat area. At least one scoop is disposed in the second inter-blade passage, the scoop defining a cavity extending radially into the outer surface of the hub relative to the nominal hub diameter.Type: ApplicationFiled: September 15, 2017Publication date: March 21, 2019Inventors: Karan ANAND, Farid ABRARI, Ernest ADIQUE, Paul AITCHISON, Daniel FUDGE, Kari HEIKURINEN, Paul STONE, Tibor URAC, Thomas VEITCH
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Publication number: 20190085704Abstract: A rotor for a gas turbine engine. The rotor includes blades circumferentially distributed around a hub. The blades have airfoils with a span defined between a root and tip, a chord defined between a leading edge and a trailing edge, and a thickness defined between a pressure side surface and suction side surface. The blades include first blades and second blades. The airfoil of the first blades has a first thickness distribution defining a first natural vibration frequency of the airfoils of the first blades. The airfoil of the second blades has a second thickness distribution defining a second natural vibration frequency different than the first natural vibration frequency. The first thickness distribution is different than the second thickness distribution along a radially-inner half of the span, and the first thickness distribution matches the second thickness distribution along a radially-outer half of the span.Type: ApplicationFiled: September 15, 2017Publication date: March 21, 2019Inventors: Thomas VEITCH, Farid ABRARI, Ernest ADIQUE, Daniel FUDGE, Kari HEIKURINEN, Paul STONE, Ignatius THERATIL, Peter TOWNSEND, Tibor URAC
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Publication number: 20190078589Abstract: A rotor for a gas turbine engine comprises a rotor having a hub and blades around the hub, and extending from the hub to tips. The tips include first and second tip portions between their respective tip leading edge and tip trailing edge. Tips are spaced from a rotational axis of the rotor by spans. A mean span of a first tip portion of a first blade is greater than a mean span of a corresponding first tip portion of a second blade. A mean span of a second tip portion the first blade is less than a mean span of a corresponding second tip portion of the second blade.Type: ApplicationFiled: September 13, 2017Publication date: March 14, 2019Inventors: Thomas VEITCH, Farid ABRARI, Ernest ADIQUE, Daniel FUDGE, Kari HEIKURINEN, Paul STONE, Ignatius THERATIL, Peter TOWNSEND, Tibor URAC
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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: 20160348692Abstract: A compressor airfoil of a gas turbine engine includes a pressure side and a suction side of the airfoil extending downstream from a stagnation point, the suction side including a suction side surface portion within a leading edge region, and a main suction side airfoil surface downstream from the suction side surface portion and extending contiguously therewith. The suction side surface portion having a compound curvature profile which includes at least a leading edge having a first curvature profile and a chamfered surface having a second curvature profile different from the first curvature profile. The chamfered surface being contiguous with and extending immediately downstream from the leading edge. The first curvature profile being curved. The second curvature profile of the chamfered surface being substantially flat and defining a substantially straight-line profile in a cross-section transverse to the span-wise axis of the airfoil.Type: ApplicationFiled: May 29, 2015Publication date: December 1, 2016Inventors: Kari HEIKURINEN, Ron DUTTON
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Patent number: 9303589Abstract: A fan for a turbofan gas turbine engine, the fan comprising a rotor hub and a plurality of radially extending fan blades integral with the hub to form an integrally bladed rotor. Each fan blade defines a leading edge. A hub radius (RHUB) is the radius of the leading edge at the hub relative to a centerline of the fan. A tip radius (RTIP) is the radius of the leading edge at a tip of the fan blade relative to the centerline of the fan. The ratio of the hub radius to the tip radius (RHUB/RTIP) is at least less than 0.29. In a particular embodiment, this ratio is between 0.25 and 0.29. In another particular embodiment, this ratio is less than or equal to 0.25.Type: GrantFiled: November 28, 2012Date of Patent: April 5, 2016Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Kari Heikurinen, Peter Townsend
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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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Patent number: 8100655Abstract: An airfoil root fillet having a predetermined compound curve profile can be flank milled with a single flank milling cutter having a generally conical flank milling portion and a rounded tip portion defining a compound curve.Type: GrantFiled: March 28, 2008Date of Patent: January 24, 2012Assignee: Pratt & Whitney Canada Corp.Inventors: Paul Stone, Dinesh Chawla, Frank Kelly, Edward Fazari, Kari Heikurinen, Ignatius Theratil
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Patent number: 8043063Abstract: A frequency mistuned integrally bladed rotor (IBR) for a gas turbine engine comprises a hub and a circumferential row of blades of varying frequency projecting integrally from the hub. Each blade in the row alternate with another blade having a different pressure surface definition but similar suction surface, leading edge and trailing edge definitions.Type: GrantFiled: March 26, 2009Date of Patent: October 25, 2011Assignee: Pratt & Whitney Canada Corp.Inventors: Frank Kelly, Kari Heikurinen, Edward Fazari, Yuhua Wu