
基本信息:
- 专利标题: TURBINE AIRFOIL TRAILING EDGE BIFURCATED COOLING HOLES
- 专利标题(中):涡轮机空气涡轮叶片偏心冷却孔
- 申请号:US13466508 申请日:2012-05-08
- 公开(公告)号:US20130302177A1 公开(公告)日:2013-11-14
- 发明人: Robert Frederick Bergholz, JR. , Daniel Lee Durstock
- 申请人: Robert Frederick Bergholz, JR. , Daniel Lee Durstock
- 主分类号: F01D5/18
- IPC分类号: F01D5/18
摘要:
A gas turbine engine turbine airfoil having pressure and suction sidewalls extending outwardly along a span and chordwise between opposite leading and trailing edges. A spanwise row of spaced apart bifurcated trailing edge cooling holes encased in the pressure sidewall end at corresponding trailing edge cooling slots extending chordally substantially to the trailing edge. Axially extending inter-hole partitions separate the cooling holes. An inlet between adjacent pairs of the inter-hole partitions includes a divergent inlet section. An axial intra-hole partition bifurcates the cooling hole into diverging upper and lower diverging sections downstream and aft of the divergent inlet section. A forward end of the intra-hole partition divides an aft end of the divergent inlet section into upper and lower inlet flowpaths leading to the upper and lower diverging sections leading into the trailing edge cooling slots.
摘要(中):
具有压力和吸力侧壁的燃气涡轮发动机涡轮机翼型件,其沿着跨越并且在相对的前缘和后缘之间沿弦向外延伸。 间隔开的分叉的后缘冷却孔,包围在压力侧壁端部的相应的后缘冷却狭槽处,其基本上延伸到后缘。 轴向延伸的孔间分隔开冷却孔。 相邻成对的孔间分隔件之间的入口包括发散入口部分。 轴向孔内分隔将冷却孔分叉成发散入口部分下游和后部的发散的上部和下部分歧部分。 孔内分隔件的前端将发散入口部分的后端分成通向通向后缘冷却槽的上部和下部分歧部分的上部和下部入口流动路径。
IPC结构图谱:
F | 机械工程;照明;加热;武器;爆破 |
--F01 | 一般机器或发动机;一般的发动机装置;蒸汽机 |
----F01D | 非变容式机器或发动机,如汽轮机 |
------F01D5/00 | 叶片;叶片的支承元件;叶片或元件的加热、隔热、冷却或防止振动装置 |
--------F01D5/02 | .叶片的支承元件,如转子 |
----------F01D5/14 | ..型式或结构 |
------------F01D5/18 | ...空心叶片;对叶片加热、隔热或冷却装置 |