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公开(公告)号：US20180134407A1
公开(公告)日：2018-05-17
申请号：US15284001
申请日：2016-10-03
Applicant: GENERAL ELECTRIC COMPANY
Abstract: A cooling system includes a first conduit positioned within a cavity and extends from a radially inner casing aperture to a radially outer casing aperture. The cooling system also includes a second conduit coupled in flow communication with the first conduit and extending into the cavity. The cooling system further includes at least one valve positioned within the first conduit and the second conduit. The at least one valve and the first conduit are configured to channel a first fluid from the radially inner casing aperture to the radially outer casing aperture during a first mode of operation. The at least one valve, the second conduit, and the first conduit are configured to channel a second fluid from the radially outer casing aperture to the cavity during a second mode of operation.
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Patent Agency Ranking
公开(公告)号：US10583933B2
公开(公告)日：2020-03-10
申请号：US15284001
申请日：2016-10-03
Applicant: GENERAL ELECTRIC COMPANY
Abstract: A cooling system includes a first conduit positioned within a cavity and extends from a radially inner casing aperture to a radially outer casing aperture. The cooling system also includes a second conduit coupled in flow communication with the first conduit and extending into the cavity. The cooling system further includes at least one valve positioned within the first conduit and the second conduit. The at least one valve and the first conduit are configured to channel a first fluid from the radially inner casing aperture to the radially outer casing aperture during a first mode of operation. The at least one valve, the second conduit, and the first conduit are configured to channel a second fluid from the radially outer casing aperture to the cavity during a second mode of operation.
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公开(公告)号：US20170210475A1
公开(公告)日：2017-07-27
申请号：US15008046
申请日：2016-01-27
Applicant: General Electric Company
Inventor： Clark George Wiberg , Shiladitya Mukherjee
CPC classification number: B64D15/04 , B64D27/16 , B64D29/00 , F02C7/047 , F05D2220/323 , F05D2240/128 , F05D2260/201
Abstract: An aircraft anti-icing system includes an inlet lip that includes an outer shell attached to a bulkhead. The inlet lip encloses an annular housing volume. The system further includes one or more vanes extending from the bulkhead into the annular housing volume. Each vane of the one or more vanes includes a first end coupled to the bulkhead, a free end extending into the annular housing volume, and a vane body extending therebetween. The one or more vanes are positioned downstream from a nozzle configured to direct a high temperature gas stream into the annular housing volume in a first direction. The one or more vanes are configured to redirect the high temperature gas stream through a first turn angle from the first direction to a second direction. The second direction is configured to reduce a direct impingement of the high temperature gas stream on an inner surface of the inlet lip.
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公开(公告)号：US10513978B2
公开(公告)日：2019-12-24
申请号：US15143770
申请日：2016-05-02
Applicant: General Electric Company
Inventor： Prashant Tiwari , Shiladitya Mukherjee , Clark George Wiberg
Abstract: An apparatus for improving heat transfer through a leading portion of an aircraft engine. The apparatus includes an annular channel that is defined by the leading portion. A source for gas that is fluidly connected to the channel and a narrow region that is defined within the annular channel.
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公开(公告)号：US10167085B2
公开(公告)日：2019-01-01
申请号：US15008046
申请日：2016-01-27
Applicant: General Electric Company
Inventor： Clark George Wiberg , Shiladitya Mukherjee
Abstract: An aircraft anti-icing system includes an inlet lip that includes an outer shell attached to a bulkhead. The inlet lip encloses an annular housing volume. The system further includes one or more vanes extending from the bulkhead into the annular housing volume. Each vane of the one or more vanes includes a first end coupled to the bulkhead, a free end extending into the annular housing volume, and a vane body extending therebetween. The one or more vanes are positioned downstream from a nozzle configured to direct a high temperature gas stream into the annular housing volume in a first direction. The one or more vanes are configured to redirect the high temperature gas stream through a first turn angle from the first direction to a second direction. The second direction is configured to reduce a direct impingement of the high temperature gas stream on an inner surface of the inlet lip.
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公开(公告)号：US20170314467A1
公开(公告)日：2017-11-02
申请号：US15143770
申请日：2016-05-02
Applicant: General Electric Company
Inventor： Prashant Tiwari , Shiladitya Mukherjee , Clark George Wiberg
IPC: F02C7/047
Abstract: An apparatus for improving heat transfer through a leading portion of an aircraft engine. The apparatus includes an annular channel that is defined by the leading portion. A source for gas that is fluidly connected to the channel and a narrow region that is defined within the annular channel.
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