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公开(公告)号：US20200256196A1
公开(公告)日：2020-08-13
申请号：US16745930
申请日：2020-01-17
摘要： Airfoils for gas turbine engines are described. The airfoils include an airfoil body extending between a platform and a tip, the airfoil body having a leading edge, a trailing edge, a pressure side, and a suction side, a serpentine cavity formed within the airfoil body and having an up-pass serpentine cavity, a down-pass serpentine cavity, and a trailing edge cavity, and a dead-end tip flag cavity extending in a direction between the leading edge and the trailing edge, the dead-end tip flag cavity arrange between the serpentine cavity and the tip, wherein the dead-end tip flag cavity ends at a dead-end wall located at a position between the leading edge and the trailing edge of the airfoil body.
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公开(公告)号：US20190323362A1
公开(公告)日：2019-10-24
申请号：US15957255
申请日：2018-04-19
发明人： Allan N. Arisi , Bret M. Teller
摘要： A turbine vane for a gas turbine engine having a plurality of cooling holes defined therein, at least some of the plurality of cooling holes being located on a leading edge of an airfoil of the turbine vane and in fluid communication with an internal cavity of the turbine vane; and a baffle insert located in the internal cavity, the baffle insert having a plurality of holes formed therein at least some of the plurality of holes of the baffle insert corresponding to the at least some of the plurality of cooling holes located in the leading edge of the turbine vane, the baffle insert being formed from a flat sheet of metal wherein the plurality of holes of the baffle insert are formed in the flat sheet of metal prior to the baffle insert being formed from the flat sheet of metal, the plurality of holes of the baffle insert being formed in the flat sheet of metal according to the coordinates of Table 1.
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公开(公告)号：US10337332B2
公开(公告)日：2019-07-02
申请号：US15053682
申请日：2016-02-25
摘要： An airfoil of a gas turbine engine includes an airfoil body having a leading edge and a trailing edge extending in a radial direction, a trailing edge cavity formed within the airfoil and proximate to the trailing edge of the airfoil, the trailing edge cavity extending from the trailing edge in a forward direction toward the leading edge, at least one set of blocking pedestals located within the trailing edge cavity, a set of circular pedestals located aftward from the at least one blocking set of pedestals, and a set of spear pedestals located aftward from the set of circular pedestals and closest to the trailing edge of the airfoil body.
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公开(公告)号：US20170292384A1
公开(公告)日：2017-10-12
申请号：US15096243
申请日：2016-04-11
发明人： James T. Auxier , Parth Jariwala , Bret M. Teller
CPC分类号： F01D5/186 , F01D5/18 , F01D9/02 , F01D11/08 , F01D25/12 , F05D2220/32 , F05D2230/21 , F05D2230/211 , F05D2240/122 , F05D2240/127 , F05D2240/304 , F05D2240/35 , F05D2260/202 , F05D2260/2212 , F23R3/002 , Y02T50/676
摘要： A casting core and/or an airfoil may comprise a tip flag cavity having a forward pedestal and a first spear pedestal disposed aft of the forward pedestal. A trailing edge discharge cavity may be separated from the tip flag cavity and include a first row of pedestals. The first row of pedestals may comprise a first racetrack pedestal. A second row of pedestals may be disposed aft of the first row of pedestals and include a second racetrack pedestal. A third row of pedestals may be disposed aft of the second row of pedestals and include a circular pedestal. A fourth row of pedestals may be disposed aft of the third row of pedestals and include a second spear pedestal.
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公开(公告)号：US20200088042A1
公开(公告)日：2020-03-19
申请号：US16675879
申请日：2019-11-06
发明人： James T. Auxier , Parth Jariwala , Bret M. Teller
摘要： A casting core and/or an airfoil may comprise a tip flag cavity having a forward pedestal and a first spear pedestal disposed aft of the forward pedestal. A trailing edge discharge cavity may be separated from the tip flag cavity and include a first row of pedestals. The first row of pedestals may comprise a first racetrack pedestal. A second row of pedestals may be disposed aft of the first row of pedestals and include a second racetrack pedestal. A third row of pedestals may be disposed aft of the second row of pedestals and include a circular pedestal. A fourth row of pedestals may be disposed aft of the third row of pedestals and include a second spear pedestal.
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公开(公告)号：US10406596B2
公开(公告)日：2019-09-10
申请号：US14702136
申请日：2015-05-01
IPC分类号： F01D5/14 , F01D5/18 , B22C9/10 , B22D15/00 , B22D17/00 , B22C9/06 , B22D25/02 , F01D5/02 , F01D9/04 , F01D11/08 , F01D25/12
摘要： A casting core for an airfoil according to an example of the present disclosure includes, among other things, a first portion extending in a first direction and corresponding to a first cavity of an airfoil. The first portion defines a reference plane along a parting line formed by a casting die. The first portion defines a plurality of grooves corresponding to a plurality of trip strips of the airfoil. Each of the plurality of grooves defines a respective groove axis, and the plurality of grooves are distributed in the first direction along a first side of the reference plane such that one or more of the groove axes are oriented with respect to a pull direction of the casting die. A method for fabricating a gas turbine engine component is also disclosed.
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公开(公告)号：US20170248021A1
公开(公告)日：2017-08-31
申请号：US15053682
申请日：2016-02-25
CPC分类号： F01D5/187 , B22C9/101 , F01D9/041 , F01D11/08 , F01D25/12 , F05D2220/32 , F05D2230/20 , F05D2230/211 , F05D2240/122 , F05D2240/304 , F05D2240/55 , F05D2260/2214 , F05D2260/22141 , Y02T50/676
摘要： An airfoil of a gas turbine engine includes an airfoil body having a leading edge and a trailing edge extending in a radial direction, a trailing edge cavity formed within the airfoil and proximate to the trailing edge of the airfoil, the trailing edge cavity extending from the trailing edge in a forward direction toward the leading edge, at least one set of blocking pedestals located within the trailing edge cavity, a set of circular pedestals located aftward from the at least one blocking set of pedestals, and a set of spear pedestals located aftward from the set of circular pedestals and closest to the trailing edge of the airfoil body.
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公开(公告)号：US20160319674A1
公开(公告)日：2016-11-03
申请号：US14702136
申请日：2015-05-01
IPC分类号： F01D5/18 , F01D9/04 , F01D11/08 , B22D17/00 , B22C9/10 , B22D15/00 , B22D25/02 , F01D5/02 , F01D25/12
CPC分类号： B22C9/101 , B22C9/06 , B22C9/103 , B22D15/00 , B22D17/00 , B22D25/02 , F01D5/02 , F01D5/14 , F01D5/147 , F01D5/187 , F01D9/041 , F01D11/08 , F01D25/12 , F05D2220/32 , F05D2230/21 , F05D2230/211 , F05D2260/202
摘要： A casting core for an airfoil according to an example of the present disclosure includes, among other things, a first portion extending in a first direction and corresponding to a first cavity of an airfoil. The first portion defines a reference plane along a parting line formed by a casting die. The first portion defines a plurality of grooves corresponding to a plurality of trip strips of the airfoil. Each of the plurality of grooves defines a respective groove axis, and the plurality of grooves are distributed in the first direction along a first side of the reference plane such that one or more of the groove axes are oriented with respect to a pull direction of the casting die. A method for fabricating a gas turbine engine component is also disclosed.
摘要翻译： 根据本公开的示例的用于翼型的铸造芯部尤其包括沿第一方向延伸并对应于翼型件的第一腔的第一部分。 第一部分沿着由铸模形成的分型线限定参考平面。 第一部分限定对应于翼型件的多个跳闸条的多个槽。 多个槽中的每一个限定相应的槽轴线，并且多个槽沿着参考平面的第一侧在第一方向上分布，使得一个或多个槽轴线相对于 铸造模具 还公开了一种用于制造燃气涡轮发动机部件的方法。
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公开(公告)号：US11148191B2
公开(公告)日：2021-10-19
申请号：US16520911
申请日：2019-07-24
IPC分类号： B22D25/02 , F01D5/14 , F01D5/18 , F01D9/04 , F01D25/12 , B22C9/10 , B22C9/06 , B22D15/00 , B22D17/00
摘要： A gas turbine engine according to an example of the present disclosure includes, among other things, a rotor and a vane spaced axially from the rotor, and a blade outer air seal spaced radially from the rotor. At least one of the rotor and the vane includes an airfoil section extending from a platform. At least one of the airfoil section, the platform and the blade outer air seal includes a first cavity extending in a first direction, the first cavity defining a reference plane along a parting line formed by a casting die, and a plurality of trip strips including a first set of trip strips distributed in the first direction along a surface of the first cavity and on a first side of the reference plane, each of the plurality of trip strips defining a respective groove axis extending longitudinally between a first end and an opposed, second end of a respective one the plurality of trip strips, and the groove axes being oriented with respect to a pull direction of the casting die. A casting core and method for fabricating a gas turbine engine component is also disclosed.
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公开(公告)号：US10677071B2
公开(公告)日：2020-06-09
申请号：US15957255
申请日：2018-04-19
发明人： Allan N. Arisi , Bret M. Teller
摘要： A turbine vane for a gas turbine engine having a plurality of cooling holes defined therein, at least some of the plurality of cooling holes being located on a leading edge of an airfoil of the turbine vane and in fluid communication with an internal cavity of the turbine vane; and a baffle insert located in the internal cavity, the baffle insert having a plurality of holes formed therein at least some of the plurality of holes of the baffle insert corresponding to the at least some of the plurality of cooling holes located in the leading edge of the turbine vane, the baffle insert being formed from a flat sheet of metal wherein the plurality of holes of the baffle insert are formed in the flat sheet of metal prior to the baffle insert being formed from the flat sheet of metal, the plurality of holes of the baffle insert being formed in the flat sheet of metal according to the coordinates of Table 1.
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