公开(公告)号：US06241468B1

公开(公告)日：2001-06-05

申请号：US09401993

申请日：1999-09-23

Applicant: Gary D Lock ,  Martin L G Oldfield

Inventor： Gary D Lock ,  Martin L G Oldfield

IPC: F01D514

CPC classification number: F01D5/186 ,  F05D2250/323

Abstract: A gas turbine engine component, typically either a turbine blade or vane or combustor, comprising a wall (40) with a first surface (39) which is adapted to be supplied with a flow of cooling air, and a second surface (38) which is adapted to be exposed to a hot gas stream (50). The wall (40) further having defined therein a plurality of passages (57), the passages (57) defined by passage walls (54), which interconnect a passage inlet (31) in said first surface (39) to a passage outlet (32) in said the second surface (38). The passages (57), cooling air and the hot gas stream (50) arranged such that in operation a flow (52) of cooling air is directed through said passages (57) to provide a flow (36) of cooling air over at least a portion of the second surface (39). The cross sectional area of each of the passages (57) progressively decreasing overall, in the direction of cooling air flow (52) through the passage (57), such that in use the flow of cooling air (52) through the passage (57) is accelerated. The passage walls (54) of the cooling passages (57) preferably diverging laterally across the wall (40) of the component whilst perpendicular to the wall (40) they converge so that overall the cross-sectional area decreases.

Abstract translation: 一种燃气涡轮发动机部件，通常是涡轮机叶片或叶片或燃烧器，其包括具有第一表面（39）的壁（40），第一表面（39）适于被供应冷却空气流，第二表面（38） 适于暴露于热气流（50）。 进一步在其中限定有多个通道（57）的壁（40），由通道壁（54）限定的通道（57），其将所述第一表面（39）中的通道入口（31）与通道出口 32）在所述第二表面（38）中。 通道（57），冷却空气和热气流（50）被布置成使得在操作中冷却空气的流动（52）被引导通过所述通道（57），以提供至少冷却空气的流（36） 第二表面（39）的一部分。 每个通道（57）的横截面积在通过通道（57）的冷却空气流（52）的方向上逐渐减小，使得在使用中通过通道（57）的冷却空气（52）的流动 ）加速。 冷却通道（57）的通道壁（54）优选地横向穿过部件的壁（40）发散，同时垂直于壁（40）会聚，使得横截面积总体减小。