| 陈强，郝晟淳，丁健，马永峰，才彦双.气冷高压涡轮模拟试验研究[J].航空发动机,2019,45(6):75-80 |
| 气冷高压涡轮模拟试验研究 |
| Simulation Test Study of Air-cooled High-pressure Turbine |
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| DOI： |
| 中文关键词: 气冷高压涡轮 冷气掺混 气动特性 动量比 冷气流量 气膜孔位置 有效效率 模拟试验 |
| 英文关键词:air-cooled high-pressure turbine cooling air mixing aerodynamic performance momentum ratio cooling air flow rate film orifice position effective efficiency simulated test |
| 基金项目:国防工程重点研究项目资助 |
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| 中文摘要: |
| 为了量化评估冷气掺混对高压涡轮性能的影响，综合分析现有设备能力，采用动量比相似的模拟方法，在2 个结构和测
试布局相同，但叶片分别为实心叶片和气冷叶片的涡轮上进行对比试验，并借此开展冷气流量、气膜孔位置因素对涡轮性能影响的
试验研究。结合试验数据对比分析不同的效率计算方法，确定有效效率为气冷涡轮效率的计算方法。试验结果表明：涡轮性能随冷
气流量的增加逐渐恶化，作功能力逐渐下降，效率降低幅度呈先减小后增大趋势；从前缘至尾缘，冷气越靠后进入主流道，气体能量
利用率越低，涡轮效率越低。 |
| 英文摘要: |
| In order to quantify and estimate the influence of cooling air mixing on the performance of high-pressure turbine and
comprehensive analyse the existing equipment capacity，based on simulation method with similar momentum ratio，comparative tests were
carried out on two turbines with the same structure and test layout，but with solid blades and air-cooled blades，respectively. Test study on
the effect of cooling air flow rate and film orifice position on turbine performance were carried out. Combined with the test data，different
efficiency calculation methods were compared and analyzed，and the calculation method which the effective efficiency was air-cooled
turbine efficiency was determined. The test results show that the turbine performance degrades gradually with the increase of cooling air flow
rate，and the working capacity decreases gradually，and the efficiency decreases at first and then increases. From the leading edge to the
trailing edge，the more backward the cooling air enters the main channel，the lower the air energy utilization rate is，and the lower the turbine
efficiency is. |
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