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公开(公告)号：US11359646B2
公开(公告)日：2022-06-14
申请号：US16555558
申请日：2019-08-29
Applicant: General Electric Company
Inventor： Sesha Subramanian , Monty Lee Shelton , Robert Proctor , Mohamed Musthafa Thoppil , Venkateswararao Gurram , Josiah Warren Joiner , Wojciech Sak
Abstract: An apparatus and method of cooling a hot portion of a gas turbine engine, such as a multi-stage compressor of a gas turbine engine, by reducing an operating air temperature in a space between a seal and a blade post of adjacent stages by routing cooling air through an inlet in the vane, passing the routed cooling air through the vane, and emitting the routed cooling air into the space.
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公开(公告)号：US10287902B2
公开(公告)日：2019-05-14
申请号：US14989088
申请日：2016-01-06
Applicant: General Electric Company
Inventor： Wojciech Sak , Timothy William Taylor , Walter Glen Crosby, IV
Abstract: A variable stator vane includes airfoil mounted to a button centered about a rotational axis and having cylindrical portion supporting airfoil and a button undercut extending away from cylindrical portion and radially inwardly from circumference of cylindrical portion. Conical portion of button circumscribed about conical axis of revolution extends away from cylindrical portion. Conical axis of revolution may be tilted with respect to and may intersect rotational axis. Airfoil may include airfoil overhang extending radially outwardly beyond circular trailing edge of button. Variable stator vane may include airfoil disposed between spaced apart outer and inner buttons centered about a rotational axis, inner button having a cylindrical portion supporting airfoil and circumscribed about rotational axis, and button undercut extending away from cylindrical portion and radially inwardly from a circumference of cylindrical portion with respect to rotational axis. Outer and inner spindles extend from outer and inner buttons and airfoil.
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公开(公告)号：US20170138372A1
公开(公告)日：2017-05-18
申请号：US14941995
申请日：2015-11-16
Applicant: General Electric Company
Inventor： Sesha Subramanian , Monty Lee Shelton , Robert Proctor , Mohamed Musthafa Thoppil , Venkateswararao Gurram , Josiah Warren Joiner , Wojciech Sak
Abstract: An apparatus and method of cooling a hot portion of a gas turbine engine, such as a multi-stage compressor of a gas turbine engine, by reducing an operating air temperature in a space between a seal and a blade post of adjacent stages by routing cooling air through an inlet in the vane, passing the routed cooling air through the vane, and emitting the routed cooling air into the space.
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Patent Agency Ranking
公开(公告)号：US12270306B2
公开(公告)日：2025-04-08
申请号：US17552294
申请日：2021-12-15
Applicant: General Electric Company
Inventor： Neelesh Sarawate , Stephan Priebe , Wojciech Sak
Abstract: An engine component with an abradable material and treatment is disclosed herein. An example engine component includes a substrate having a first thickness and defining at least a first substrate surface, the substrate extending along an axial direction, an abradable material on the first substrate surface, the abradable material defining a first abradable material surface, a second abradable material surface spaced radially apart from the first abradable material surface and defining a second thickness, and a treatment, the treatment extending from the first abradable material surface through at least a portion of the first thickness of the substrate.
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公开(公告)号：US10451084B2
公开(公告)日：2019-10-22
申请号：US14941995
申请日：2015-11-16
Applicant: General Electric Company
Inventor： Sesha Subramanian , Monty Lee Shelton , Robert Proctor , Mohamed Musthafa Thoppil , Venkateswararao Gurram , Josiah Warren Joiner , Wojciech Sak
Abstract: An apparatus and method of cooling a hot portion of a gas turbine engine, such as a multi-stage compressor of a gas turbine engine, by reducing an operating air temperature in a space between a seal and a blade post of adjacent stages by routing cooling air through an inlet in the vane, passing the routed cooling air through the vane, and emitting the routed cooling air into the space.
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公开(公告)号：US20230184125A1
公开(公告)日：2023-06-15
申请号：US17552294
申请日：2021-12-15
Applicant: General Electric Company
Inventor： Neelesh Sarawate , Stephan Priebe , Wojciech Sak
CPC classification number: F01D11/122 , F01D25/24 , F05D2230/31 , F05D2230/90 , F05D2240/14 , F05D2240/55 , F05D2250/294 , F05D2300/6111
Abstract: An engine component with an abradable material and treatment is disclosed herein. An example engine component includes a substrate having a first thickness and defining at least a first substrate surface, the substrate extending along an axial direction, an abradable material on the first substrate surface, the abradable material defining a first abradable material surface, a second abradable material surface spaced radially apart from the first abradable material surface and defining a second thickness, and a treatment, the treatment extending from the first abradable material surface through at least a portion of the first thickness of the substrate.
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公开(公告)号：US20200011347A1
公开(公告)日：2020-01-09
申请号：US16555558
申请日：2019-08-29
Applicant: General Electric Company
Inventor： Sesha Subramanian , Monty Lee Shelton , Robert Proctor , Mohamed Musthafa Thoppil , Venkateswararao Gurram , Josiah Warren Joiner , Wojciech Sak
Abstract: An apparatus and method of cooling a hot portion of a gas turbine engine, such as a multi-stage compressor of a gas turbine engine, by reducing an operating air temperature in a space between a seal and a blade post of adjacent stages by routing cooling air through an inlet in the vane, passing the routed cooling air through the vane, and emitting the routed cooling air into the space.
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公开(公告)号：US20170191367A1
公开(公告)日：2017-07-06
申请号：US14989088
申请日：2016-01-06
Applicant: General Electric Company
Inventor： Wojciech Sak , Timothy William Taylor , Walter Glen Crosby, IV
IPC: F01D9/04
CPC classification number: F01D9/041 , F01D17/162 , F04D29/563 , F05D2220/32 , F05D2250/232 , F05D2250/90
Abstract: A variable stator vane includes airfoil mounted to a button centered about a rotational axis and having cylindrical portion supporting airfoil and a button undercut extending away from cylindrical portion and radially inwardly from circumference of cylindrical portion. Conical portion of button circumscribed about conical axis of revolution extends away from cylindrical portion. Conical axis of revolution may be tilted with respect to and may intersect rotational axis. Airfoil may include airfoil overhang extending radially outwardly beyond circular trailing edge of button. Variable stator vane may include airfoil disposed between spaced apart outer and inner buttons centered about a rotational axis, inner button having a cylindrical portion supporting airfoil and circumscribed about rotational axis, and button undercut extending away from cylindrical portion and radially inwardly from a circumference of cylindrical portion with respect to rotational axis. Outer and inner spindles extend from outer and inner buttons and airfoil.
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