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公开(公告)号：US20130309079A1
公开(公告)日：2013-11-21
申请号：US13662284
申请日：2012-10-26
Applicant: General Electric Company
IPC: F01D25/00
CPC classification number: F01D9/041 , F01D5/189 , F01D25/00 , F05B2230/237 , F05D2240/81 , F05D2260/201 , Y02T50/676
Abstract: A turbine nozzle segment includes: an arcuate outer band segment; an airfoil-shaped turbine vane extending radially inward from the outer band segment, the turbine vane having a hollow interior; an impingement baffle assembly secured to the outer band so as to define an impingement cavity in cooperation with the outer band segment, wherein the impingement baffle assembly has at least one impingement hole formed therein which is arranged to direct cooling air at the outer band segment; and at least one impingement insert having at least one impingement hole formed therein disposed in the interior of the turbine vane, the impingement insert mating with an opening in the impingement baffle assembly such that the impingement baffle is isolated from direct fluid communication with the impingement cavity.
Abstract translation: 涡轮喷嘴段包括：弓形外带段; 所述翼型涡轮叶片从所述外带段径向向内延伸，所述涡轮叶片具有中空的内部; 冲击挡板组件，其固定到所述外部带，以便与所述外部带段协调地限定冲击腔，其中所述冲击挡板组件具有形成在其中的至少一个冲击孔，所述至少一个冲击孔被布置成在所述外部带段处引导冷却空气; 并且至少一个冲击插入件具有形成在其中的至少一个冲击孔，其设置在涡轮叶片的内部，冲击插入件与冲击挡板组件中的开口相配合，使得冲击挡板与冲击腔直接流体连通隔离 。
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公开(公告)号：US09726024B2
公开(公告)日：2017-08-08
申请号：US14368962
申请日：2012-12-21
Applicant: GENERAL ELECTRIC COMPANY
CPC classification number: F01D5/188 , F01D5/189 , F01D9/02 , F05D2250/185 , F05D2260/201 , Y02T50/676
Abstract: An airfoil cooling circuit includes an impingement cooling circuit and a serpentine cooling circuit. An airfoil for use in a gas turbine engine having a cooling circuit which includes an impingement cooling circuit and a serpentine cooling circuit.
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公开(公告)号：US20140348636A1
公开(公告)日：2014-11-27
申请号：US14368962
申请日：2012-12-21
Applicant: GENERAL ELECTRIC COMPANY
CPC classification number: F01D5/188 , F01D5/189 , F01D9/02 , F05D2250/185 , F05D2260/201 , Y02T50/676
Abstract: An airfoil cooling circuit includes an impingement cooling circuit and a serpentine cooling circuit. An airfoil for use in a gas turbine engine having a cooling circuit which includes an impingement cooling circuit and a serpentine cooling circuit
Abstract translation: 翼型冷却回路包括冲击冷却回路和蛇形冷却回路。 一种在具有冷却回路的燃气涡轮发动机中使用的翼型件，该冷却回路包括冲击冷却回路和蛇形冷却回路
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公开(公告)号：US09845691B2
公开(公告)日：2017-12-19
申请号：US13662284
申请日：2012-10-26
Applicant: General Electric Company
CPC classification number: F01D9/041 , F01D5/189 , F01D25/00 , F05B2230/237 , F05D2240/81 , F05D2260/201 , Y02T50/676
Abstract: A turbine nozzle segment includes: an arcuate outer band segment; an airfoil-shaped turbine vane extending radially inward from the outer band segment, the turbine vane having a hollow interior; an impingement baffle assembly secured to the outer band so as to define an impingement cavity in cooperation with the outer band segment, wherein the impingement baffle assembly has at least one impingement hole formed therein which is arranged to direct cooling air at the outer band segment; and at least one impingement insert having at least one impingement hole formed therein disposed in the interior of the turbine vane, the impingement insert mating with an opening in the impingement baffle assembly such that the impingement baffle is isolated from direct fluid communication with the impingement cavity.
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