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公开(公告)号：US20210054747A1
公开(公告)日：2021-02-25
申请号：US16545417
申请日：2019-08-20
Applicant: United Technologies Corporation
Inventor： Brandon W. Spangler , David R. Pack
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：US11286793B2
公开(公告)日：2022-03-29
申请号：US16545451
申请日：2019-08-20
Applicant: United Technologies Corporation
Inventor： Brandon W. Spangler , David R. Pack
Abstract: 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.
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公开(公告)号：US20210148235A1
公开(公告)日：2021-05-20
申请号：US16683640
申请日：2019-11-14
Applicant: United Technologies Corporation
Inventor： Brandon W. Spangler , David R. Pack , JinQuan Xu
IPC: F01D5/18
Abstract: 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.
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公开(公告)号：US20210140323A1
公开(公告)日：2021-05-13
申请号：US16682453
申请日：2019-11-13
Applicant: United Technologies Corporation
Inventor： Brandon W. Spangler , David R. Pack
IPC: F01D5/18
Abstract: 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.
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公开(公告)号：US20200024962A1
公开(公告)日：2020-01-23
申请号：US16397265
申请日：2019-04-29
Applicant: United Technologies Corporation
Inventor： Pitchaiah Vijay Chakka , James D. Hill , David R. Pack
Abstract: 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.
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Patent Agency Ranking
公开(公告)号：US12000305B2
公开(公告)日：2024-06-04
申请号：US16682453
申请日：2019-11-13
Applicant: United Technologies Corporation
Inventor： Brandon W. Spangler , David R. Pack
IPC: F01D5/18
CPC classification number: F01D5/189 , F05D2220/32 , F05D2250/75 , F05D2260/201 , F05D2260/22141
Abstract: 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.
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公开(公告)号：US20200277858A1
公开(公告)日：2020-09-03
申请号：US16289341
申请日：2019-02-28
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Brandon W. Spangler , David R. Pack
Abstract: 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.
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公开(公告)号：US10316671B2
公开(公告)日：2019-06-11
申请号：US14802512
申请日：2015-07-17
Applicant: United Technologies Corporation
Inventor： Pitchaiah Vijay Chakka , James D. Hill , David R. Pack
Abstract: 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 includes a first portion near the airfoil base with a first density and includes 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.
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9.发明申请公开(公告)号：US20160186666A1
公开(公告)日：2016-06-30
申请号：US14844097
申请日：2015-09-03
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Julian Partyka , David R. Pack , James D. Hill
CPC classification number: F02C9/18 , F01D11/001 , F01D11/006 , F01D11/04 , F02C6/18 , F02C7/12 , F05D2220/32 , F05D2260/20
Abstract: A turbine section for a gas turbine engine includes a first rotor assembly with a first rotor assembly bleed air source and an aft cavity that is in fluid communication with the first rotor assembly bleed air source. A second rotor assembly includes a forward cavity. A vane bleed air source is in fluid communication with the forward cavity. A seal extends between the first rotor assembly and the second rotor assembly.
Abstract translation: 用于燃气涡轮发动机的涡轮部分包括具有第一转子组件放气源的第一转子组件和与第一转子组件放气源流体连通的后腔。 第二转子组件包括前腔。 叶片放气源与前腔流体连通。 密封件在第一转子组件和第二转子组件之间延伸。
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公开(公告)号：US20210054746A1
公开(公告)日：2021-02-25
申请号：US16545451
申请日：2019-08-20
Applicant: United Technologies Corporation
Inventor： Brandon W. Spangler , David R. Pack
Abstract: 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
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