公开(公告)号：US20130051974A1

公开(公告)日：2013-02-28

申请号：US13218224

申请日：2011-08-25

申请人： Kin Poon ,  Jeff Howe ,  Michael T. Todd Barton ,  Frank Mignano ,  Mahmoud Mansour ,  Nick Nolcheff ,  Scott Taylor ,  Steve Trzcinski ,  Ardeshir Riahi ,  Jeff Guymon ,  Alan Hemmingson ,  Alex Mirzamoghadam

发明人： Kin Poon ,  Jeff Howe ,  Michael T. Todd Barton ,  Frank Mignano ,  Mahmoud Mansour ,  Nick Nolcheff ,  Scott Taylor ,  Steve Trzcinski ,  Ardeshir Riahi ,  Jeff Guymon ,  Alan Hemmingson ,  Alex Mirzamoghadam

IPC分类号： F04D27/02 ,  F01D5/08

CPC分类号： F01D25/14 ,  F04D29/162 ,  F04D29/4206

摘要： Gas turbine engines and methods for cooling components thereof with mid-impeller bleed (MIB) cooling air having a pressure are provided. The gas turbine engine has a compressor comprising an impeller body and an impeller shroud at least partially surrounding the impeller body. The impeller shroud has a plurality of MIB openings disposed therein. At least one edge treatment is provided thereto. The edge treatment substantially preserves pressure of the cooling air during entrance into and discharge out of the MIB opening. The plurality of MIB openings may be extended MIB openings in a thickened impeller shroud. The centerline of the MIB openings may be oriented to be substantially aligned with an averaged local absolute flow velocity vector of the cooling air at the inlet section of the MIB opening in order to extract cooling air in a direction that has a vector component in a tangential, an axial, and a radial flow direction.

摘要翻译： 提供了燃气涡轮发动机及其具有中间叶轮排出（MIB）冷却空气的组件的组件的压力。 燃气涡轮发动机具有压缩机，该压缩机包括至少部分地围绕叶轮本体的叶轮本体和叶轮护罩。 叶轮护罩具有设置在其中的多个MIB开口。 向其提供至少一个边缘处理。 边缘处理在进入和排出MIB开口时基本上保持冷却空气的压力。 多个MIB开口可以在增厚的叶轮护罩中延伸MIB开口。 MIB开口的中心线可以被定向为与MIB开口的入口部分处的冷却空气的平均局部绝对流速矢量基本对齐，以便沿着具有向心分量的向量分量的方向提取冷却空气 ，轴向和径向流动方向。