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公开(公告)号：US20170335700A1
公开(公告)日：2017-11-23
申请号：US15159935
申请日：2016-05-20
Applicant: United Technologies Corporation
Inventor： Russell J. Bergman , Brett Alan Bartling
CPC classification number: F01D9/041 , F01D5/18 , F01D9/065 , F05D2220/32 , F05D2230/10 , F05D2230/232 , F05D2230/237 , F05D2240/10 , F05D2240/121 , F05D2240/81 , F05D2250/324 , F05D2260/202
Abstract: A stator for a gas turbine engine includes a stator vane, a first cooling passage located at the stator to provide a cooling fluid flow to a first portion of the stator, and a second cooling passage located at the stator to provide a cooling fluid flow to a second portion of the stator. A connection passage extends at least partially through the stator to connect a first cooling passage inlet of the first cooling passage to a second cooling passage inlet of the second cooling passage. The cooling fluid flow is directed from a common cooling flow source into the first cooling passage and the second cooling passage via the first cooling passage inlet.
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公开(公告)号：US10352182B2
公开(公告)日：2019-07-16
申请号：US15159935
申请日：2016-05-20
Applicant: United Technologies Corporation
Inventor： Russell J. Bergman , Brett Alan Bartling
Abstract: A stator for a gas turbine engine includes a stator vane, a first cooling passage located at the stator to provide a cooling fluid flow to a first portion of the stator, and a second cooling passage located at the stator to provide a cooling fluid flow to a second portion of the stator. A connection passage extends at least partially through the stator to connect a first cooling passage inlet of the first cooling passage to a second cooling passage inlet of the second cooling passage. The cooling fluid flow is directed from a common cooling flow source into the first cooling passage and the second cooling passage via the first cooling passage inlet.
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公开(公告)号：US11073024B2
公开(公告)日：2021-07-27
申请号：US16220396
申请日：2018-12-14
Applicant: United Technologies Corporation
Inventor： Christopher Perron , Justin M. Aniello , Shawn M. McMahon , Mohamed Hassan , Ricardo Trindade , Steven Bruce Gautschi , David Barger , Brett Alan Bartling , Nicholas J. Madonna , Robin Prenter , Ryan Lundgreen , Christopher Cosher
Abstract: A vane ring for a gas turbine engine component includes a multiple of vanes that extend between an inner vane platform and an outer vane platform, each of the multiple of vanes contains an airfoil cooling circuit that receives cooing airflow through a feed passage located in the outer vane platform and an extension from the outer vane platform, the extension comprises a metering passage in communication with the feed passage.
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公开(公告)号：US20160312631A1
公开(公告)日：2016-10-27
申请号：US15103561
申请日：2014-11-06
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Russell J. Bergman , Charles C. Wu , Brett Alan Bartling
CPC classification number: F01D9/06 , F01D9/041 , F01D11/001 , F01D11/04 , F01D25/12 , F05D2220/32 , F05D2240/12 , F05D2240/81
Abstract: A vane comprises an airfoil extending from a radially outer platform to a radially inner platform. A pair of legs extend radially inwardly from the radially inner platform, and an air flow passage extends through the radially outer platform, through the airfoil, and into a chamber defined between the pair of legs. One of the pair of legs includes a plurality of injector holes, configured to allow air from the radially outer platform to pass outwardly of the holes. A gas turbine engine is also disclosed.
Abstract translation: 叶片包括从径向外部平台延伸到径向内部平台的翼型件。 一对腿从径向内部平台径向向内延伸，并且空气流动通道穿过径向外部平台延伸通过翼型件，并进入限定在该对腿部之间的腔室中。 一对腿中的一个包括多个喷射器孔，其构造成允许来自径向外平台的空气通过孔的外部。 还公开了一种燃气涡轮发动机。
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Patent Agency Ranking
公开(公告)号：US11053808B2
公开(公告)日：2021-07-06
申请号：US16790890
申请日：2020-02-14
Applicant: United Technologies Corporation
Inventor： Russell J. Bergman , Charles C. Wu , Brett Alan Bartling
Abstract: A vane comprises an airfoil extending from a radially outer platform to a radially inner platform. A pair of legs extend radially inwardly from the radially inner platform, and an air flow passage extends through the radially outer platform, through the airfoil, and into a chamber defined between the pair of legs. One of the pair of legs includes a plurality of injector holes, configured to allow air from the radially outer platform to pass outwardly of the holes. A gas turbine engine is also disclosed.
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公开(公告)号：US20190071979A1
公开(公告)日：2019-03-07
申请号：US15790505
申请日：2017-10-23
Applicant: United Technologies Corporation
Inventor： Shawn M. McMahon , Christopher Whitfield , Kristopher K. Anderson , Jason B. Moran , Brett Alan Bartling , Christopher Perron , Justin M. Aniello , Stephanie Tanner , Dominic J. Mongillo, JR.
Abstract: A vane cluster for a gas turbine engine includes an outer diameter platform and an inner diameter platform. A plurality of vanes span from the outer diameter platform to the inner diameter platform. At least one inbound region is defined between a first vane of the plurality of vanes and a second vane of the plurality of vanes. The first vane includes a suction side facing the inbound region. Each of the vanes includes a leading edge core passage and a trailing edge core passage. A plurality of electrical discharge machined (EDM) holes are disposed within at least 0.500 inches (12.7 mm) of a leading edge of the first vane. Each of the EDM holes connect a leading edge core passage of the vane to an exterior surface of the vane.
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公开(公告)号：US11078796B2
公开(公告)日：2021-08-03
申请号：US16220400
申请日：2018-12-14
Applicant: United Technologies Corporation
Inventor： Christopher Perron , Justin M. Aniello , Shawn M. McMahon , Ricardo Trindade , Steven Bruce Gautschi , David Barger , Brett Alan Bartling , Nicholas J. Madonna , Robin Prenter , Ryan Lundgreen , Christopher Cosher , Mohamed Hassan
Abstract: A vane ring for a gas turbine engine includes a multiple of vanes that extend between the inner vane platform and the outer vane platform, each of the multiple of vanes contains an airfoil cooling circuit that receives cooling airflow through a respective one of a multiple of feed passages; a multiple of metering passages in the outer vane platform, each of the multiple of metering passages in communication with the respective one of the multiple of feed passages; and a multiple of secondary passages in the outer vane platform, each of the multiple of secondary passages in communication with the respective one of the multiple of metering passages.
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公开(公告)号：US11008872B2
公开(公告)日：2021-05-18
申请号：US16220398
申请日：2018-12-14
Applicant: United Technologies Corporation
Inventor： Christopher Perron , Justin M. Aniello , Shawn M. McMahon , Ricardo Trindade , Steven Bruce Gautschi , David Barger , Brett Alan Bartling , Nicholas J. Madonna , Robin Prenter , Ryan Lundgreen , Christopher Cosher , Mohamed Hassan
Abstract: A vane ring for a gas turbine engine component includes a multiple of vanes that extend between an inner vane platform and an outer vane platform, each of the multiple of vanes contains an airfoil cooling circuit that receives cooling airflow through a feed passage located in the outer vane platform and an extension from the outer vane platform, the extension comprises a metering passage in communication with the feed passage.
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公开(公告)号：US20190071978A1
公开(公告)日：2019-03-07
申请号：US15790423
申请日：2017-10-23
Applicant: United Technologies Corporation
Inventor： Shawn M. McMahon , Christopher Whitfield , Kristopher K. Anderson , Jason B. Moran , Brett Alan Bartling , Christopher Perron , Justin M. Aniello , Stephanie Tanner
Abstract: A vane cluster for a gas turbine engine including an inner diameter platform and an outer diameter platform. A plurality of vanes span from the inner diameter platform to the outer diameter platform. An inbound region is defined between a first vane and a second vane of the plurality of vanes. A plenum is defined in the inner diameter platform at the inbound region. The plenum including a plurality of film cooling holes fluidly connecting the plenum to a primary flowpath. A feed hole connects the plenum to a core cooling cavity of one of the first vane and the second vane to the plenum.
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