摘要
为了研究射流模拟方法对气膜冷却流动的分析精度,以某型发动机涡轮叶片中截面叶型的片体模型为研究对象,对比了不同叶型位置、射流角度及孔径下的冷却射流与主流燃气的掺混损失和流量变化情况,并与真实冷却气膜孔的计算结果进行了对比。不同叶型位置处的仿真结果对比情况表明:射流模型在压力面侧及吸力面前段可以较为准确地捕捉不同叶型位置处的流动损失变化情况,总压损失绝对值的最大偏差仅有0.02%,而在吸力面后段,射流法的分析结果则出现了较为明显的偏离;不同倾斜角和孔径的对比结果表明:由于并未精确模拟气膜孔出口的肾形对涡,简化射流法在气膜孔出口附近低估了实际流动的损失,但随着流动的发展,冷却流动与主流流动沿流向的掺混损失占据主导,此时简化射流法可以较为准确地捕捉包括损失峰值在内的相对压力损失变化。
In order to study the accuracy of jet-flow method for film cooling flow simulation,a certain aero engine turbine mid-span cascade was used as research object,mixing losses and mass flow change of cooling injection and main gas stream under different blade positions,jet angles and hole diameters were analyzed and compared with real cooling film hole calculation result.Simulation results show that at different blade positions,jet-flow model can accurately capture the changes in flow losses on the pressure side and front section of the suction surface with a maximum absolute deviation of total pressure loss of 0.02%,meanwhile,a significant deviation is observed on the rear section of suction surface by the jetflow method.Comparative results at different elevation angles and hole diameters indicate that the simplified jet-flow method tends to underestimate the actual flow loss near the outlet of film hole due to the lack of accurate simulation of the kidney-shaped vortex of film outlet.As the injection flow develops,the mixing loss of cooling flow and mainstream flow along the flow direction becomes the dominant factor,the simplified jet-flow method can accurately predict the changes of relative pressure losses,including position of the loss peak.
作者
王士骥
田雨
曾静茹
WANG Shiji;TIAN Yu;ZENG Jingru(AECC Commercial Aircraft Engine Co.,Ltd.,Shanghai,China,Post Code:200241)
出处
《热能动力工程》
CAS
CSCD
北大核心
2024年第8期58-66,共9页
Journal of Engineering for Thermal Energy and Power
基金
国家科技重大专项(2019-Ⅱ-0008-0028)。
关键词
气冷涡轮
模拟方法
冷却流动
射流法
air-cooled turbine
simulation approach
cooling flow
jet-flow method
