An equivalent no-perforated plate concept is introduced in the stress-strain analysis for densely-distributed film cooling holes on turbine blades of gas turbine engines.
以带气膜冷却孔的航空燃气涡轮发动机涡轮叶片为研究背景，引入了等效概念对密布小孔结构进行了详细的应力-应变分析。
An equivalent no-perforated plate concept is introduced in the stress-strain analysis for densely-distributed film cooling holes on turbine blades of gas turbine engines.
以带气膜冷却孔的航空燃气涡轮发动机涡轮叶片为研究背景，引入了等效概念对密布小孔结构进行了详细的应力-应变分析。
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