Patents by Inventor David R. Pack
David R. Pack 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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Publication number: 20240151146Abstract: Airfoils and core assemblies for such airfoils are described. The airfoils include a leading edge cavity defined, in part, by a leading edge interior rib and a trailing edge cavity defined, in part, by a trailing edge interior rib. A plurality of pressure side cavities are defined by pressure side skin cavity walls with at least one pressure side skin cavity wall not extending to the suction side wall. A plurality of suction side cavities are defined by suction side skin cavity walls with at least one suction side skin cavity wall not extending to the pressure side wall. A main body cavity extends between the leading edge interior rib and the trailing edge interior rib and the plurality of side cavities are arranged in a staggered pattern to define the bounds of the main body cavity.Type: ApplicationFiled: January 4, 2024Publication date: May 9, 2024Inventors: Brandon W. Spangler, David R. Pack
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Patent number: 11970954Abstract: An airfoil includes an airfoil wall that defines a leading end, a trailing end, and first and second sides that join the leading end and the trailing end. A rib connects the first and second sides of the airfoil wall. The rib defines a tube portion that circumscribes a rib passage, and first and second connector arms that solely join the tube portion to, respectively, the first and second sides of the airfoil wall.Type: GrantFiled: October 24, 2022Date of Patent: April 30, 2024Assignee: RTX CORPORATIONInventors: Brandon W. Spangler, David R. Pack
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Patent number: 11952911Abstract: An airfoil include an airfoil wall that defines a leading end, a trailing end, a first side wall, and a second side wall. A rib connects the first and second side walls of the airfoil wall. The rib includes a first arm by which the rib is solely connected to the first side wall, and second and third arms by which the rib is solely connected to the second side wall.Type: GrantFiled: November 14, 2019Date of Patent: April 9, 2024Assignee: RTX CORPORATIONInventors: Brandon W. Spangler, David R. Pack, JinQuan Xu
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Publication number: 20240102391Abstract: A turbine engine airfoil element has a plurality of main body passageways along a camber line and having two or more chordwise distributed protuberant portions with necks between the protuberant portions. A plurality of skin passageways include: at least one first skin passageway each nested between a first of the pressure side and the suction side and two adjacent main body passageways; and a plurality of second skin passageways each nested between first of the pressure side and the suction side and two said protuberant portions of a corresponding main body passageway.Type: ApplicationFiled: September 26, 2023Publication date: March 28, 2024Applicant: RTX CorporationInventors: Brandon W. Spangler, David R. Pack
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Patent number: 11905849Abstract: Airfoils and core assemblies for such airfoils are described. The airfoils include a leading edge cavity defined, in part, by a leading edge interior rib and a trailing edge cavity defined, in part, by a trailing edge interior rib. A plurality of pressure side cavities are defined by pressure side skin cavity walls with at least one pressure side skin cavity wall not extending to the suction side wall. A plurality of suction side cavities are defined by suction side skin cavity walls with at least one suction side skin cavity wall not extending to the pressure side wall. A main body cavity extends between the leading edge interior rib and the trailing edge interior rib and the plurality of side cavities are arranged in a staggered pattern to define the bounds of the main body cavity.Type: GrantFiled: October 17, 2022Date of Patent: February 20, 2024Assignee: RTX CORPORATIONInventors: Brandon W. Spangler, David R. Pack
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Publication number: 20230160308Abstract: An airfoil includes an airfoil wall that defines a leading end, a trailing end, and first and second sides that join the leading end and the trailing end. A rib connects the first and second sides of the airfoil wall. The rib defines a tube portion that circumscribes a rib passage, and first and second connector arms that solely join the tube portion to, respectively, the first and second sides of the airfoil wall.Type: ApplicationFiled: October 24, 2022Publication date: May 25, 2023Inventors: Brandon W. Spangler, David R. Pack
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Publication number: 20230130326Abstract: Airfoils and core assemblies for such airfoils are described. The airfoils include a leading edge cavity defined, in part, by a leading edge interior rib and a trailing edge cavity defined, in part, by a trailing edge interior rib. A plurality of pressure side cavities are defined by pressure side skin cavity walls with at least one pressure side skin cavity wall not extending to the suction side wall. A plurality of suction side cavities are defined by suction side skin cavity walls with at least one suction side skin cavity wall not extending to the pressure side wall. A main body cavity extends between the leading edge interior rib and the trailing edge interior rib and the plurality of side cavities are arranged in a staggered pattern to define the bounds of the main body cavity.Type: ApplicationFiled: October 17, 2022Publication date: April 27, 2023Inventors: Brandon W. Spangler, David R. Pack
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Patent number: 11629602Abstract: Airfoil for gas turbine engines are described. The airfoils have internal walls and internal cavities. A leading edge cavity is defined within the airfoil body along a leading edge and a leading edge feed cavity is arranged aft of the leading edge cavity. A bent leading edge rib is arranged between the leading edge cavity and the leading edge feed cavity. A main body cavity is arranged aft of the leading edge feed cavity and defined at least in part by two interior ribs that define a part of the leading edge feed cavity. The main body cavity is fluidly connected to the leading edge feed cavity by an interior fluid connection through the intersection of the two interior ribs. A shield cavity is arranged to thermally shield the leading edge feed cavity from heat pickup along the suction side of the airfoil body.Type: GrantFiled: June 16, 2022Date of Patent: April 18, 2023Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Brandon W. Spangler, David R. Pack
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Publication number: 20220403746Abstract: Airfoil for gas turbine engines are described. The airfoils have internal walls and internal cavities. A leading edge cavity is defined within the airfoil body along a leading edge and a leading edge feed cavity is arranged aft of the leading edge cavity. A bent leading edge rib is arranged between the leading edge cavity and the leading edge feed cavity. A main body cavity is arranged aft of the leading edge feed cavity and defined at least in part by two interior ribs that define a part of the leading edge feed cavity. The main body cavity is fluidly connected to the leading edge feed cavity by an interior fluid connection through the intersection of the two interior ribs. A shield cavity is arranged to thermally shield the leading edge feed cavity from heat pickup along the suction side of the airfoil body.Type: ApplicationFiled: June 16, 2022Publication date: December 22, 2022Inventors: Brandon W. Spangler, David R. Pack
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Patent number: 11480059Abstract: An airfoil includes an airfoil wall that defines a leading end, a trailing end, and first and second sides that join the leading end and the trailing end. A rib connects the first and second sides of the airfoil wall. The rib defines a tube portion that circumscribes a rib passage, and first and second connector arms that solely join the tube portion to, respectively, the first and second sides of the airfoil wall.Type: GrantFiled: August 20, 2019Date of Patent: October 25, 2022Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Brandon W. Spangler, David R. Pack
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Patent number: 11286793Abstract: An airfoil includes an airfoil wall that defines a leading end, a trailing end, and first and second sides joining the leading end and the trailing end. First and second ribs each connect the first and second sides of the airfoil wall. Each of the first and second ribs define a tube portion that circumscribes a rib passage and includes cooling apertures, and first and second connector arms that solely join the tube portion to, respectively, the first and second sides of the airfoil wall. The airfoil wall and the first and second ribs bound a cooling channel there between. The cooling apertures of the first and second ribs open at the cooling channel such that there is a cooling circuit in which the rib passages of the first and second ribs are fluidly connected through the cooling apertures and the cooling channel.Type: GrantFiled: August 20, 2019Date of Patent: March 29, 2022Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Brandon W. Spangler, David R. Pack
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Patent number: 11209221Abstract: A modified shaped heat exchanger hot air inlet and hot air outlet comprising a first heat exchanger manifold surrounding said hot air inlet and a second heat exchanger manifold surrounding said hot air outlet; an array of shaped inlets and shaped outlets, each of said shaped inlets and shaped outlets being configured to align vertices with thermal load directions responsive to a thermal expansion mismatch between the hot air inlet and hot air outlet and respective first heat exchanger manifold and second heat exchanger manifold.Type: GrantFiled: April 21, 2020Date of Patent: December 28, 2021Assignee: Raytheon Technologies CorporationInventors: Brandon W. Spangler, David R. Pack, William P. Stillman
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Publication number: 20210325129Abstract: A modified shaped heat exchanger hot air inlet and hot air outlet comprising a first heat exchanger manifold surrounding said hot air inlet and a second heat exchanger manifold surrounding said hot air outlet; an array of shaped inlets and shaped outlets, each of said shaped inlets and shaped outlets being configured to align vertices with thermal load directions responsive to a thermal expansion mismatch between the hot air inlet and hot air outlet and respective first heat exchanger manifold and second heat exchanger manifold.Type: ApplicationFiled: April 21, 2020Publication date: October 21, 2021Inventors: Brandon W. Spangler, David R. Pack, William P. Stillman
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Patent number: 11149550Abstract: A blade for use with a gas turbine engine includes an attachment and an airfoil. The airfoil further includes a suction side wall configured to be exposed to less pressure than the pressure side wall during operation of the gas turbine engine. The blade also includes a plurality of intersecting ribs transitioning from an airfoil cross sectional geometry to an attachment cross section geometry.Type: GrantFiled: February 7, 2019Date of Patent: October 19, 2021Assignee: Raytheon Technologies CorporationInventors: Brandon W. Spangler, David R. Pack
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Publication number: 20210148235Abstract: An airfoil include an airfoil wall that defines a leading end, a trailing end, a first side wall, and a second side wall. A rib connects the first and second side walls of the airfoil wall. The rib includes a first arm by which the rib is solely connected to the first side wall, and second and third arms by which the rib is solely connected to the second side wall.Type: ApplicationFiled: November 14, 2019Publication date: May 20, 2021Inventors: Brandon W. Spangler, David R. Pack, JinQuan Xu
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Publication number: 20210140323Abstract: An airfoil includes an airfoil wall that defines a leading end, a trailing end, a pressure side, a suction side, and a mean line. First and second ribs each connect the pressure side and the suction side. Each of the first and second ribs define a tube portion that circumscribes a rib passage, and first and second connector arms that solely join the tube portion to, respectively, the pressure side and the suction side. The first rib, the second rib, and the airfoil wall bound a continuous cooling channel there between. The continuous cooling channel has a pressure side portion to the pressure side of the mean line and a suction side portion to the suction side of the mean line. The pressure side portion and the suction side portion each have a cross-sectioned shape selected from an L-shape, a T-shape, and an l-shape.Type: ApplicationFiled: November 13, 2019Publication date: May 13, 2021Inventors: Brandon W. Spangler, David R. Pack
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Patent number: 10954799Abstract: A blade for a gas turbine engine includes a body that includes an airfoil that extends in a radial direction from a 0% span position near an airfoil base to a 100% span position at an airfoil tip. The airfoil has a leading edge and a trailing edge that define the true chord length. The airfoil includes a first portion near the airfoil base with a first density and a second portion near the airfoil tip with a second density. The second density is less than the first density. The second portion includes an increasing true chord length in the radial direction. The second portion is in the range of 90% span to 100% span.Type: GrantFiled: April 29, 2019Date of Patent: March 23, 2021Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Pitchaiah Vijay Chakka, James D. Hill, David R. Pack
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Publication number: 20210054746Abstract: An airfoil includes an airfoil wall that defines a leading end, a trailing end, and first and second sides joining the leading end and the trailing end. First and second ribs each connect the first and second sides of the airfoil wall. Each of the first and second ribs define a tube portion that circumscribes a rib passage and includes cooling apertures, and first and second connector arms that solely join the tube portion to, respectively, the first and second sides of the airfoil wall. The airfoil wall and the first and second ribs bound a cooling channel there between.Type: ApplicationFiled: August 20, 2019Publication date: February 25, 2021Inventors: Brandon W. Spangler, David R. Pack
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Publication number: 20210054747Abstract: An airfoil includes an airfoil wall that defines a leading end, a trailing end, and first and second sides that join the leading end and the trailing end. A rib connects the first and second sides of the airfoil wall. The rib defines a tube portion that circumscribes a rib passage, and first and second connector arms that solely join the tube portion to, respectively, the first and second sides of the airfoil wall.Type: ApplicationFiled: August 20, 2019Publication date: February 25, 2021Inventors: Brandon W. Spangler, David R. Pack
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Patent number: 10871074Abstract: An airfoil for use with a gas turbine engine includes a pressure side wall and a suction side wall. The suction side wall is configured to be exposed to less pressure than the pressure side wall during operation of the gas turbine engine. The blade also includes a plurality of ribs forming a plurality of trapezoidal shaped cavities to receive a cooling airflow. The plurality of ribs being shaped in a way to allow for thermal growth of the airfoil, while minimizing stress in the airfoil.Type: GrantFiled: February 28, 2019Date of Patent: December 22, 2020Assignee: Raytheon Technologies CorporationInventors: Brandon W Spangler, David R Pack