公开(公告)号：EP3196414A1

公开(公告)日：2017-07-26

申请号：EP17152351.7

申请日：2017-01-20

申请人： United Technologies Corporation

发明人： AUXIER, James Tilsley ,  ZELESKY, Mark F. ,  TELLER, Bret M. ,  JARIWALA, Parth ,  MONGILLO, Dominic J.

IPC分类号： F01D5/18 ,  F01D5/30 ,  F02C3/16

CPC分类号： F01D5/187 ,  F01D9/02 ,  F01D25/12 ,  F04D29/324 ,  F04D29/542 ,  F04D29/582 ,  F05D2220/32 ,  F05D2250/185 ,  F05D2260/202 ,  F05D2260/22141 ,  F05D2260/606 ,  Y02T50/676

摘要： An airfoil (201; 301; 401; 501) of a gas turbine engine is provided including a leading edge (212; 312) extending in a radial direction, a tip (232; 332; 432; 532) extending in an axial direction from the leading edge, a first rib (232; 332; 432; 532) extending radially within the airfoil, the leading edge and the first rib defining a leading edge cavity (220; 320; 420; 520) within the airfoil, a second rib (234; 334), the second rib and the first rib defining a serpentine cavity (228; 328; 428; 528) therein, a third rib (236; 336; 436; 536) extending axially within the tip, a flag tip cavity (226; 326; 426; 526) defined by the third rib, the leading edge, and the tip, the leading edge cavity fluidly connected to the flag tip cavity, and a bypass aperture (240; 340; 440; 540) formed between the first rib and the third rib, the bypass aperture configured to fluidly connect the serpentine cavity with the flag tip cavity.

摘要翻译： 提供了一种燃气涡轮发动机的翼型件（201; 301; 401; 501），该翼型件包括在径向方向上延伸的前缘（212; 312），沿轴向方向延伸的尖端（232; 332; 432; 532） 所述前缘，在所述翼型中径向延伸的第一肋（232; 332; 432; 532），所述前缘和所述第一肋在所述翼型内限定出前缘腔（220; 320; 420; 520）;第二肋 （234; 334），所述第二肋和所述第一肋在其中限定了蛇形腔（228; 328; 428; 528），在所述尖端内轴向延伸的第三肋（236; 336; 436; 536） 由所述第三肋，所述前缘和所述尖端限定的所述前缘腔（226; 326; 426; 526），所述前缘腔流体地连接至所述旗尖端腔;以及旁通孔（240; 340; 440; 540） 所述第一肋和所述第三肋，所述旁路孔配置成将所述蛇形腔与所述旗尖端腔流体连接。

公开(公告)号：EP3049640A1

公开(公告)日：2016-08-03

申请号：EP14845261.8

申请日：2014-08-26

申请人： United Technologies Corporation

发明人： LEWIS, Scott D. ,  MONGILLO, JR. Dominic J. ,  ZELESKY, Mark F. ,  TELLER, Bret M. ,  DEIBEL, Russell ,  GLEINER, Matthew S.

IPC分类号： F01D25/12 ,  F01D11/08 ,  F02C7/12 ,  F02C7/28 ,  F04D29/58 ,  F04D29/08

CPC分类号： F01D9/041 ,  F01D5/02 ,  F01D11/08 ,  F01D11/24 ,  F02C3/04 ,  F04D29/321 ,  F04D29/542 ,  F04D29/584 ,  F05D2220/32 ,  F05D2240/11 ,  F05D2240/12 ,  F05D2240/35 ,  F05D2240/80 ,  F05D2240/81 ,  F05D2250/12 ,  F05D2260/201 ,  Y02T50/676

摘要： A vane according to an exemplary aspect of the present disclosure includes, among other things, a platform extending from an edge face and between spaced apart lateral faces and an airfoil extending outwardly from the platform. The platform includes at least one ejection port in the edge face and at least one passage connected to the at least one ejection port.