Patents by Inventor Kyle C. Lana
Kyle C. Lana 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: 11286809Abstract: An airfoil may include an airfoil body, a root and a platform disposed between the airfoil body and the root. The platform may have a first mating surface and a second mating surface. The platform may include a pocket defined by an inner diameter surface of the platform proximate the first mating surface. A channel may be defined in the platform with an outlet of the channel defined in the second mating surface.Type: GrantFiled: April 25, 2017Date of Patent: March 29, 2022Assignee: Raytheon Technologies CorporationInventors: Scott D Lewis, Kyle C Lana
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Patent number: 11021976Abstract: A gas-turbine engine is provided. The gas-turbine engine comprises a high pressure turbine with an aft blade platform. A static structure may be disposed aft of the high pressure turbine and proximate a cavity defined by the aft blade platform. A vane of the static structure may have a vane platform with a shaped tip extending into the cavity.Type: GrantFiled: September 23, 2015Date of Patent: June 1, 2021Assignee: Raytheon Technologies CorporationInventors: Steven D. Porter, John T. Ols, Kyle C. Lana
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Patent number: 10941663Abstract: Airfoils for gas turbine engines are provided. The airfoils include a body extending between leading and trailing edges in an axial direction, between pressure and suction sides in a circumferential direction, and between a root and tip in a radial direction. A first transitioning leading edge cavity is located adjacent one of the sides proximate the root of the body and transitions axially toward the leading edge as the first transitioning leading edge cavity extends radially toward the tip. A second transitioning leading edge cavity is adjacent the other side and adjacent the leading edge proximate the root of the body and transitions axially toward the trailing edge as the second transitioning leading edge cavity extends radially toward the tip. A portion of the second transitioning leading edge cavity shields a portion of the first transitioning leading edge cavity proximate the root of the body.Type: GrantFiled: May 7, 2018Date of Patent: March 9, 2021Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Timothy J. Jennings, Tracy A. Propheter-Hinckley, Kyle C. Lana
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Patent number: 10907479Abstract: Airfoils for gas turbine engines are provided. The airfoils include an airfoil body extending between a leading edge and a trailing edge in an axial direction, between a pressure side and a suction side in a circumferential direction, and between a root and a tip in a radial direction, a first transitioning leading edge cavity located proximate the leading edge proximate the root of the airfoil body and transitioning axially toward the trailing edge as the first transitioning leading edge cavity extends radially toward the tip, and a second transitioning leading edge cavity located aft of the first transitioning leading edge cavity proximate the root of the airfoil body and transitioning axially toward the leading edge as the second transitioning leading edge cavity extends radially toward the tip. The second transitioning leading edge cavity includes an impingement sub-cavity and a film sub-cavity along the leading edge and proximate the tip.Type: GrantFiled: May 7, 2018Date of Patent: February 2, 2021Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Timothy J. Jennings, Tracy A. Propheter-Hinckley, Kyle C. Lana
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Patent number: 10907482Abstract: An example turbine includes a turbine disk and a turbine blade. The turbine disk includes a plurality of lugs and a plurality of slots. Each of the plurality of lugs is located between two of the plurality of slots. Each of the plurality of lugs includes a tab that extends radially outwardly from an end of the lug. The tab has a first section having an upper surface and a second section having an upper surface. The upper surface of the first section is inclined greater than the upper surface of the second section, and the upper surface of the first section of the tab defines a contour. The turbine blade includes a root received in one of the plurality of slots and a platform, and the platform has a lower surface defining a contour.Type: GrantFiled: September 10, 2018Date of Patent: February 2, 2021Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Daniel A. Snyder, Jaimie Schweitzer, Jonathan Perry Sandoval, Edwin Otero, Kyle C. Lana, Scott D. Virkler
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Patent number: 10815788Abstract: A component for a gas turbine engine, the component having: a cooling slot located on a surface of the component, the cooling slot being defined by a plurality of diffuser portions each extending from a respective one of a plurality of cooling openings providing cooling fluid to the cooling slot.Type: GrantFiled: January 30, 2017Date of Patent: October 27, 2020Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Scott D. Lewis, Kyle C. Lana
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Patent number: 10801331Abstract: A gas turbine engine blade includes a blade portion having a leading edge and a trailing edge. A first surface connects the leading edge to the trailing edge and a second surface connects the leading edge to the trailing edge. A tip section is located at a first end of the blade portion and includes a pocket protruding into the tip section from an outermost end of the tip section. The pocket has a first side wall adjacent the first surface and a second side wall adjacent the second surface. At least one of the first side wall and the second side wall have a curve distinct from a curve of the corresponding adjacent surface.Type: GrantFiled: June 7, 2016Date of Patent: October 13, 2020Assignee: Raytheon Technologies CorporationInventors: Patrick D. Couture, Scott D. Lewis, Kyle C. Lana
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Patent number: 10753210Abstract: Airfoils for gas turbine engines are provided. The airfoils include an airfoil body extending between leading and trailing edges in an axial direction, between pressure and suction sides in a circumferential direction, and between a root and tip in a radial direction, a first shielding sidewall cavity located adjacent one of the pressure and suction sides proximate the root of the airfoil body and extending radially toward the tip, a second shielding sidewall cavity located adjacent the other of the pressure and suction sides proximate the root of the airfoil body and extending radially toward the tip, and a shielded sidewall cavity located between the first shielding sidewall cavity and the second shielding sidewall cavity, wherein the shielded sidewall cavity is not adjacent either of the pressure or suction sides proximate the root and transitions to be proximate at least one of the pressure and suction sides proximate the tip.Type: GrantFiled: May 2, 2018Date of Patent: August 25, 2020Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Timothy J. Jennings, Tracy A. Propheter-Hinckley, Kyle C. Lana
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Patent number: 10677066Abstract: A rotor blade for a gas turbine engine is provided. The rotor blade having: an attachment; an airfoil extending from the attachment to a tip; and a tip shelf located in a surface of the tip proximate to a pressure side of the airfoil, wherein the tip shelf has a ledge portion extending from the pressure side to a wall portion extending upwardly from the ledge portion to the tip and wherein the wall portion is configured to have a convex portion with respect to the pressure side of the airfoil as it extends from a leading edge to a trailing edge of the airfoil.Type: GrantFiled: February 8, 2016Date of Patent: June 9, 2020Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Scott D. Lewis, Kyle C. Lana
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Patent number: 10648353Abstract: An airfoil stage of a turbine engine includes an upstream airfoil assembly, a downstream airfoil assembly in rotational relationship to the upstream airfoil assembly and a rim seal assembly integrated therebetween. The rim seal assembly may include a sloped downstream portion of a platform of the upstream airfoil assembly, an upstream segment of a platform of the downstream airfoil assembly and a nub that projects radially outward from the upstream segment. The downstream portion and the upstream segment are spaced from one-another defining a cooling cavity therebetween for the flow of cooling air. The portion and segment overlap axially such that the nub is axially aligned to the downstream portion for improved cooling effectiveness and a reduction of core airflow into the cooling cavity.Type: GrantFiled: November 16, 2015Date of Patent: May 12, 2020Assignee: United Technologies CorporationInventors: Andrew S. Aggarwala, Russell J. Bergman, Mark A. Boeke, Kyle C. Lana, Daniel A. Snyder
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Patent number: 10557354Abstract: A gas turbine engine component includes spaced apart walls that provide a cooling passage that extends in a first direction. A cross-over rib joins the walls and extends along the first direction. The cross-over rib has holes that extend in a second direction transverse to the first direction. A row of at least one pedestal joins the walls and extends along the first direction. The row and the cross-over rib overlap one another in the second direction.Type: GrantFiled: August 13, 2014Date of Patent: February 11, 2020Assignee: United Technologies CorporationInventors: Edwin Otero, Kyle C. Lana
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Patent number: 10513931Abstract: An airfoil is provided. The airfoil comprises a crossover and an impingement cavity in fluid communication with the crossover and having an internal surface. At least a portion of the internal surface comprises an undulating internal surface. A plurality of trip strips may be disposed on the at least a portion of the internal surface to define the undulating internal surface. A gas turbine engine and an internally-cooled engine part are also provided.Type: GrantFiled: December 18, 2015Date of Patent: December 24, 2019Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Scott D. Lewis, Kyle C. Lana
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Publication number: 20190338648Abstract: Airfoils for gas turbine engines are provided. The airfoils include an airfoil body extending between a leading edge and a trailing edge in an axial direction, between a pressure side and a suction side in a circumferential direction, and between a root and a tip in a radial direction, a first transitioning leading edge cavity located proximate the leading edge proximate the root of the airfoil body and transitioning axially toward the trailing edge as the first transitioning leading edge cavity extends radially toward the tip, and a second transitioning leading edge cavity located aft of the first transitioning leading edge cavity proximate the root of the airfoil body and transitioning axially toward the leading edge as the second transitioning leading edge cavity extends radially toward the tip. The second transitioning leading edge cavity includes an impingement sub-cavity and a film sub-cavity along the leading edge and proximate the tip.Type: ApplicationFiled: May 7, 2018Publication date: November 7, 2019Inventors: Timothy J. Jennings, Tracy A. Propheter-Hinckley, Kyle C. Lana
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Publication number: 20190338652Abstract: Airfoils for gas turbine engines are provided. The airfoils include an airfoil body extending between leading and trailing edges in an axial direction, between pressure and suction sides in a circumferential direction, and between a root and tip in a radial direction, a first shielding sidewall cavity located adjacent one of the pressure and suction sides proximate the root of the airfoil body and extending radially toward the tip, a second shielding sidewall cavity located adjacent the other of the pressure and suction sides proximate the root of the airfoil body and extending radially toward the tip, and a shielded sidewall cavity located between the first shielding sidewall cavity and the second shielding sidewall cavity, wherein the shielded sidewall cavity is not adjacent either of the pressure or suction sides proximate the root and transitions to be proximate at least one of the pressure and suction sides proximate the tip.Type: ApplicationFiled: May 2, 2018Publication date: November 7, 2019Inventors: Timothy J. Jennings, Tracy A. Propheter-Hinckley, Kyle C. Lana
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Publication number: 20190338649Abstract: Airfoils for gas turbine engines are provided. The airfoils include a body extending between leading and trailing edges in an axial direction, between pressure and suction sides in a circumferential direction, and between a root and tip in a radial direction. A first transitioning leading edge cavity is located adjacent one of the sides proximate the root of the body and transitions axially toward the leading edge as the first transitioning leading edge cavity extends radially toward the tip. A second transitioning leading edge cavity is adjacent the other side and adjacent the leading edge proximate the root of the body and transitions axially toward the trailing edge as the second transitioning leading edge cavity extends radially toward the tip. A portion of the second transitioning leading edge cavity shields a portion of the first transitioning leading edge cavity proximate the root of the body.Type: ApplicationFiled: May 7, 2018Publication date: November 7, 2019Inventors: Timothy J. Jennings, Tracy A. Propheter-Hinckley, Kyle C. Lana
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Patent number: 10253635Abstract: A turbine blade according to an example of the present disclosure includes, among other things, a platform extending from a root section, an airfoil section extending radially from the platform to an airfoil tip, a plurality of cooling passages defined in an external wall of the airfoil tip, the plurality of cooling passages extending radially between the airfoil tip and a cavity in the airfoil section bounded by the external wall, and each of the plurality of cooling passages defining an inlet port along the cavity and an exit port adjacent the airfoil tip, and at least one internal feature within each of the plurality of cooling passages that meter flow to the respective exit port.Type: GrantFiled: April 30, 2018Date of Patent: April 9, 2019Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Dominic J. Mongillo, Jr., Jeffrey R. Levine, Kyle C. Lana, Sasha M. Moore
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Publication number: 20190010810Abstract: An example turbine includes a turbine disk and a turbine blade. The turbine disk includes a plurality of lugs and a plurality of slots. Each of the plurality of lugs is located between two of the plurality of slots. Each of the plurality of lugs includes a tab that extends radially outwardly from an end of the lug. The tab has a first section having an upper surface and a second section having an upper surface. The upper surface of the first section is inclined greater than the upper surface of the second section, and the upper surface of the first section of the tab defines a contour. The turbine blade includes a root received in one of the plurality of slots and a platform, and the platform has a lower surface defining a contour.Type: ApplicationFiled: September 10, 2018Publication date: January 10, 2019Inventors: Daniel A. Snyder, Jaimie Schweitzer, Jonathan Perry Sandoval, Edwin Otero, Kyle C. Lana, Scott D. Virkler
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Publication number: 20180306058Abstract: An airfoil may include an airfoil body, a root and a platform disposed between the airfoil body and the root. The platform may have a first mating surface and a second mating surface. The platform may include a pocket defined by an inner diameter surface of the platform proximate the first mating surface. A channel may be defined in the platform with an outlet of the channel defined in the second mating surface.Type: ApplicationFiled: April 25, 2017Publication date: October 25, 2018Applicant: United Technologies CorporationInventors: Scott D Lewis, Kyle C. Lana
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Publication number: 20180245470Abstract: A turbine blade according to an example of the present disclosure includes, among other things, a platform extending from a root section, an airfoil section extending radially from the platform to an airfoil tip, a plurality of cooling passages defined in an external wall of the airfoil tip, the plurality of cooling passages extending radially between the airfoil tip and a cavity in the airfoil section bounded by the external wall, and each of the plurality of cooling passages defining an inlet port along the cavity and an exit port adjacent the airfoil tip, and at least one internal feature within each of the plurality of cooling passages that meter flow to the respective exit port.Type: ApplicationFiled: April 30, 2018Publication date: August 30, 2018Inventors: Dominic J. Mongillo, JR., Jeffrey R. Levine, Kyle C. Lana, Sasha M. Moore
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Publication number: 20180216472Abstract: A component for a gas turbine engine, the component having: a cooling slot located on a surface of the component, the cooling slot being defined by a plurality of diffuser portions each extending from a respective one of a plurality of cooling openings providing cooling fluid to the cooling slot.Type: ApplicationFiled: January 30, 2017Publication date: August 2, 2018Inventors: Scott D. Lewis, Kyle C. Lana