Aerodynamic and heat transfer performance measurements for double wall cooled turbine vanes in a hot cascade
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摘要:
针对采用E3发动机高压涡轮导叶叶型面和典型冲击-气膜双层壁冷却结构的综合冷效试验件，在栅前总温
1073 K、栅前总压0.9 MPa高温高压状态气热耦合扇形叶栅环境下开展叶表气动和传热特征分布测量试验研究。通过优化设计试验段主气流道，合理布置温度、静压测试叶片，实现中间叶片和相邻叶片良好的主气周期性特征，进而在单次气热耦合综合冷效试验中同时获得有效的试验件叶型面等熵马赫数分布和温度分布。试验测量得到流量比6.4%～10%、落压比1.28～2.08、温比1.5～2.3范围内有气膜孔叶片和无气膜孔叶片表面马赫数分布。试验结果显示，研究中采用的试验段设计方法和测点布置方法得到的设计点状态叶表大部分测点等熵马赫数和E3发动机涡轮环吹试验结果偏差小于0.05。相同工况下有气膜孔和无气膜孔叶片表面等熵马赫数分布特征较接近，大部分测点马赫数偏差小于0.03。Abstract:A hot cascade facility equipped with an annular cascade sector of double wall impinge-ment film cooled vanes of energy effective engine (E3) high pressure turbine was used to determine the local gas side temperature and static pressure simultaneously for inlet gas temperature of
1073 K and gas pressure of 0.9 MPa. The cascade gas flow path and positioning of temperature and pressure instrumented test vanes were optimized for the validity of simultaneous measurement of airfoil surface aerodynamic and heat transfer performance in a single cooling effectiveness test and the refinement of the flow periodicity of both middle test vane and adjacent vanes. Airfoil mid-span surface isentropic Mach number was measured for vane with film cooling and non-film cooling for mass flow ratios in the range of 6.4%—10%, gas pressure ratios in the range of 1.28—2.08 and temperature ratios in the range of 1.5—2.3. The airfoil isentropic Mach number of design operating condition measured over the test vane in annular cascade sector compared very favorably with E3 high pressure turbine component test, with the difference less than 0.05. Isentropic Mach number of film cooled vane and non-film cooled vane also agreed well, with the difference of most region less than 0.03. -
图 7 单通道扇形叶栅计算模型及网格
Figure 7. Model and grid for single passage annular cascade sector simulation
图 8 叶表中截面等熵马赫数分布
Figure 8. Isentropic Mach number distributions around the airfoil surface
图 10 不同叶片中截面等熵马赫数分布
Figure 10. Isentropic Mach number distributions on different vanes
图 11 不同模型流道中截面等熵马赫数分布云图
Figure 11. Isentropic Mach number contours for passage mid-sections of different models
图 12 尾缘下游2 mm截面等熵马赫数分布云图
Figure 12. Isentropic Mach number contours of 2 mm downstream trailing edge
图 13 尾缘下游10 mm截面等熵马赫数分布云图
Figure 13. Isentropic Mach number contours of 10 mm downstream trailing edge
图 15 不同试验段栅后测量截面等熵马赫数分布对比（Tt4=1 073 K）
Figure 15. Isentropic Mach number distributions in instrumented plane of different test sections （Tt4=1 073 K）
图 16 扇形叶栅和环形叶栅叶表中截面等熵马赫数分布
Figure 16. Isentropic Mach number distributions around the airfoil surface in annular cascade sector and annular cascade
图 17 无气膜孔叶片不同落压比下等熵马赫数分布
Figure 17. Isentropic Mach number distributions of non-film cooled vane for different pressures ratios
图 18 不同落压比下等熵马赫数分布（Tt4=1 073 K）
Figure 18. Isentropic Mach number distributions for different pressures ratios （Tt4=1 073 K）
图 19 不同流量比下等熵马赫数分布（Tt4=1 073 K）
Figure 19. Isentropic Mach number distributions for different mass flow ratios （Tt4=1 073 K）
图 20 不同温比下叶表中截面温度分布
Figure 20. Airfoil temperature distributions for different temperature ratios
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