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公开(公告)号：US11970954B2
公开(公告)日：2024-04-30
申请号：US17971938
申请日：2022-10-24
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： Brandon W. Spangler , David R. Pack
CPC classification number: F01D5/188 , F01D5/141 , F05D2220/323 , F05D2240/301 , F05D2240/35 , F05D2250/185
Abstract: 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.
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公开(公告)号：US20230160308A1
公开(公告)日：2023-05-25
申请号：US17971938
申请日：2022-10-24
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： Brandon W. Spangler , David R. Pack
CPC classification number: F01D5/188 , F01D5/141 , F05D2220/323 , F05D2240/35 , F05D2240/301 , F05D2250/185
Abstract: 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.
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Patent Agency Ranking
公开(公告)号：US11629602B2
公开(公告)日：2023-04-18
申请号：US17841839
申请日：2022-06-16
Applicant: Raytheon Technologies Corporation
Inventor： Brandon W. Spangler , David R. Pack
IPC: F01D5/18
Abstract: 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.
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公开(公告)号：US11209221B2
公开(公告)日：2021-12-28
申请号：US16854661
申请日：2020-04-21
Applicant: Raytheon Technologies Corporation
Inventor： Brandon W. Spangler , David R. Pack , William P. Stillman
Abstract: 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.
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公开(公告)号：US20210325129A1
公开(公告)日：2021-10-21
申请号：US16854661
申请日：2020-04-21
Applicant: Raytheon Technologies Corporation
Inventor： Brandon W. Spangler , David R. Pack , William P. Stillman
Abstract: 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.
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公开(公告)号：US20230130326A1
公开(公告)日：2023-04-27
申请号：US17967252
申请日：2022-10-17
Applicant: Raytheon Technologies Corporation
Inventor： Brandon W. Spangler , David R. Pack
Abstract: 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.
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公开(公告)号：US20220403746A1
公开(公告)日：2022-12-22
申请号：US17841839
申请日：2022-06-16
Applicant: Raytheon Technologies Corporation
Inventor： Brandon W. Spangler , David R. Pack
IPC: F01D5/18
Abstract: 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.
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