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公开(公告)号：US11021966B2
公开(公告)日：2021-06-01
申请号：US16393849
申请日：2019-04-24
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Nicholas J. Madonna , Daniel P. Preuss , Kristopher K. Anderson
Abstract: A gas turbine engine includes a compressor section rotatable about an axis, a combustor in fluid communication with the compressor section, and a turbine section in fluid communication with the combustor. The turbine section includes a vane assembly including a radially outer platform with respect to the axis. A first airfoil extend from the radially outer platform to a radially inner platform. A rail extends radially inward from the inner platform, and a connected passage includes an airfoil passage within the first airfoil. A platform passage is located within the inner platform, and a rail passage is located within the rail. The airfoil passage, the platform passage, and the rail passage are fluidly connected.
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公开(公告)号：US09982560B2
公开(公告)日：2018-05-29
申请号：US14599075
申请日：2015-01-16
Applicant: United Technologies Corporation
Inventor： Mark A. Boeke , Kristopher K. Anderson , Jeffrey J. De Gray , Jeffrey R. Levine , Sarah Riley , Richard M. Salzillo, Jr.
CPC classification number: F01D25/12 , F01D9/023 , F01D9/04 , F01D9/06 , F05D2240/81 , Y02T50/676
Abstract: An airfoil platform includes a platform body having an arcuate base defining a centerline axis. A rail extends radially outboard from a side of the arcuate base. A feed orifice is defined at least partially in the rail. The inner diameter edge of an axially facing opening of the feed orifice is spaced apart radially outboard of an outer diameter surface of the arcuate base. A method for manufacturing an airfoil platform includes providing an airfoil platform body and forming the feed orifice through the rail. Forming the feed orifice through the rail includes forming the feed orifice radially outboard of and spaced apart from the outer diameter surface of the arcuate base.
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公开(公告)号：US20160208627A1
公开(公告)日：2016-07-21
申请号：US14599075
申请日：2015-01-16
Applicant: United Technologies Corporation
Inventor： Mark A. Boeke , Kristopher K. Anderson , Jeffrey J. De Gray , Jeffrey R. Levine , Sarah Riley , Richard M. Salzillo, JR.
IPC: F01D9/02
CPC classification number: F01D25/12 , F01D9/023 , F01D9/04 , F01D9/06 , F05D2240/81 , Y02T50/676
Abstract: An airfoil platform includes a platform body having an arcuate base defining a centerline axis. A rail extends radially outboard from a side of the arcuate base. A feed orifice is defined at least partially in the rail. The inner diameter edge of an axially facing opening of the feed orifice is spaced apart radially outboard of an outer diameter surface of the arcuate base. A method for manufacturing an airfoil platform includes providing an airfoil platform body and forming the feed orifice through the rail. Forming the feed orifice through the rail includes forming the feed orifice radially outboard of and spaced apart from the outer diameter surface of the arcuate base.
Abstract translation: 翼型平台包括具有限定中心线轴线的弓形基部的平台本体。 轨道从弓形底座的一侧沿径向外侧延伸。 进料口至少部分地限定在轨道中。 进料孔的轴向面向的开口的内径边缘在弧形底座的外径表面的径向外侧间隔开。 一种用于制造翼型平台的方法包括提供翼型平台本体并通过导轨形成进料口。 通过导轨形成进料孔包括在弓形底座的外径表面径向地形成进料孔并且间隔开。
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Patent Agency Ranking
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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公开(公告)号：US20200340362A1
公开(公告)日：2020-10-29
申请号：US16393849
申请日：2019-04-24
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Nicholas J. Madonna , Daniel P. Preuss , Kristopher K. Anderson
Abstract: A gas turbine engine includes a compressor section rotatable about an axis, a combustor in fluid communication with the compressor section, and a turbine section in fluid communication with the combustor. The turbine section includes a vane assembly including a radially outer platform with respect to the axis. A first airfoil extend from the radially outer platform to a radially inner platform. A rail extends radially inward from the inner platform, and a connected passage includes an airfoil passage within the first airfoil. A platform passage is located within the inner platform, and a rail passage is located within the rail. The airfoil passage, the platform passage, and the rail passage are fluidly connected.
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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：US09803488B2
公开(公告)日：2017-10-31
申请号：US14590317
申请日：2015-01-06
Applicant: United Technologies Corporation
Inventor： Sarah Riley , Kristopher K. Anderson
CPC classification number: F01D9/041 , F01D5/186 , F01D25/12 , F05D2250/74 , F05D2260/202 , Y02T50/673 , Y02T50/676
Abstract: A vane includes a pair of airfoils that have a plurality of film cooling holes that extend through an exterior surface of the airfoils. Each plurality of film cooling holes break through the exterior surface at geometric coordinates in accordance with Cartesian coordinate values of X, Y and Z as set forth in Table 1. Each geometric coordinates is measured from a reference point on a leading edge rail of a platform of the vane.
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公开(公告)号：US20150211376A1
公开(公告)日：2015-07-30
申请号：US14590317
申请日：2015-01-06
Applicant: United Technologies Corporation
Inventor： Sarah Riley , Kristopher K. Anderson
IPC: F01D9/02
CPC classification number: F01D9/041 , F01D5/186 , F01D25/12 , F05D2250/74 , F05D2260/202 , Y02T50/673 , Y02T50/676
Abstract: A vane includes a pair of airfoils that have a plurality of film cooling holes that extend through an exterior surface of the airfoils. Each plurality of film cooling holes break through the exterior surface at geometric coordinates in accordance with Cartesian coordinate values of X, Y and Z as set forth in Table 1. Each geometric coordinates is measured from a reference point on a leading edge rail of a platform of the vane.
Abstract translation: 叶片包括具有延伸穿过翼型件的外表面的多个薄膜冷却孔的一对翼型件。 每个多个薄膜冷却孔根据表1所示的X，Y和Z的笛卡尔坐标值以几何坐标突破外表面。每个几何坐标是从平台的前缘导轨上的参考点测量的 的叶片。
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