Research on aerodynamic optimization design of variable geometry turbine with large flow adjustment range
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摘要:
大流量调节范围变几何涡轮是未来先进变循环发动机的关键部件之一，本文采用数值模拟方法对某流量调节范围超过170%的单级变几何涡轮在大流量调节时的流动损失特征开展分析，并基于损失来源对涡轮的子午流道、速度三角形、导叶及动叶叶型进行了优化设计。结果表明：优化后该涡轮在100%～170%流量调节范围内的效率均获得提高，其中小流量点涡轮效率相较于优化前提高了8.8%。较大的前缘直径和负攻角叶型设计有利于降低小流量点的叶型损失；导叶子午流道平直设计相较收缩设计，显著减小了导叶叶尖和叶根间隙，有效减小了泄漏损失；增大动叶出口马赫数有利于降低动叶叶根端壁损失，转子效率得到提高。
Abstract:Variable geometry turbine with large flow regulation range is a crucial component of advanced variable cycle engine in the future. Numerical simulation was employed to analyze the flow loss characteristics of a single-stage variable geometry turbine with a flow regulation range exceeding 170% during extensive flow regulation, and the meridian flow channel, velocity triangle, guide vane and rotor blade profile of the turbine were optimized based on the loss source. The results showed that the efficiency of the optimized turbine was improved within the range of 100%—170% flow regulation, and the efficiency of the turbine at small flow points was 8.8% higher than that before optimization. The design of larger leading-edge diameter and negative angle of attack could help reduce the blade profile loss at small flow rate. Compared with the contraction design, the guide vane meridian channel flat design significantly reduced the tip and root clearance of the guide vane and effectively cut down the leakage loss. Increasing the outlet Mach number of the rotor could help reduce the end wall loss of the rotor blade root and improve the rotor efficiency.
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图 4 可调叶栅叶片表面压力分布试验与数值模拟结果
Figure 4. Experimental and numerical simulation results of pressure distribution on the surface of adjustable cascades
图 5 导叶调节前后端壁间隙分布图
Figure 5. Distribution diagram of end wall clearance before and after guide vane adjustment
图 7 小流量点叶中马赫数云图
Figure 7. Mach number cloud diagram of the middle section of the blade in small flow conditions
图 11 优化前后小流量点间隙对比图
Figure 11. Gap comparison diagram of small flow point before and after optimization
图 12 优化前后导叶出口总压分布云图
Figure 12. Total pressure distribution cloud map at the stator outlet before and after optimization
图 14 优化前后设计点速度三角形
Figure 14. Velocity triangle of design point before and after optimization
图 15 小流量点10%叶高马赫数分布云图
Figure 15. Mach number distribution cloud diagram of 10% blade height under small flow condition
图 16 CASE 1与CASE 2转子域子午流线对比图
Figure 16. Comparison of rotor meridian streamlines of CASE 1 and CASE 2
图 17 CASE 2与CASE 3导叶叶型对比图
Figure 17. Comparison of stator profiles of CASE 2 and CASE 3
图 18 CASE 2与CASE 3导叶叶中马赫数分布云图
Figure 18. The mid-section Mach distribution of the stators of CASE 2 and CASE 3
图 20 动叶攻角优化前后动叶叶中马赫数云图
Figure 20. Mach number cloud diagram of the middle section of the rotor blades before and after the optimization
图 22 优化前后小流量点导叶出口熵分布云图
Figure 22. Entropy distribution of guide vane outlet under small flow conditions before and after optimization
图 23 优化前后小流量点动叶子午面流线图
Figure 23. Meridian surface streamline of rotor domain under small flow conditions before and after optimization
表 1 基础方案涡轮级几何参数
Table 1. Basic scheme turbine stage geometric parameters
参数 数值 静叶 动叶 叶片数 42 72 轮毂比 0.429 0.453 展弦比 4.81 6.82 稠度 1.447 1.345 安装角/（°） 43.3 63.1 
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表 2 涡轮典型工况条件
Table 2. Typical working conditions of turbine
工况 标况换算流量/（kg/s） 膨胀比 1 34.27 2.157 2 28.37 1.253 3 33.98 1.930 4 33.45 1.983 5 44.01 1.694 6 43.49 1.709 7 40.65 1.801 8 48.76 1.555 9 49.26 1.510 10 48.07 1.384 11 50.01 1.600 12 50.01 1.600 13 50.02 1.600 14 49.94 1.600
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表 3 导叶间隙存在时涡轮流量和效率变化表
Table 3. Turbine flow and efficiency changes in the presence of guide vane clearance
参数 数值 大流量点 小流量点 泄漏流量/（kg/s） 0.371 3.377 效率变化/% −2.3 −7.0 涡轮效率/% 87.47 74.23
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表 4 涡轮方案
Table 4. Turbine scheme
编号 涡轮方案 CASE 0 基础方案 CASE 1 CASE 0+子午流道优化 CASE 2 CASE 1+增大动叶出口马赫数 CASE 3 CASE 2+导叶叶型优化 CASE 4 CASE 3+动叶攻角优化
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表 5 子午流道优化前后涡轮部分气动参数
Table 5. Aerodynamic parameters of the turbine part before and after the meridian flow channel optimization
方案 工况 效率/% 导叶总压恢复系数 CASE 0_无间隙 大流量点 89.77 0.9887 小流量点 81.23 0.9614 CASE 1_无间隙 大流量点 91.34 0.9892 小流量点 81.95 0.9585 CASE 0_全间隙 大流量点 87.47 0.9834 小流量点 74.23 0.9494 CASE 1_全间隙 大流量点 90.26 0.9864 小流量点 81.18 0.9506
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表 6 增大动叶出口马赫数前后涡轮设计点参数
Table 6. Design parameters of the turbine before and after increasing the outlet Mach number
参数 数值 CASE 1 CASE 2 流量系数 1.10 1.30 轴向速比 1.265 1.290 轮毂半径/m 0.2012 0.2424 导叶出口速度c1/（m/s） 709.6 717.6 导叶出口气流角α1/（°） 30.4 34.4 导叶喉道面积/m2 0.2432 0.2394 导叶喉道面积相对变化/% 100 98.44
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表 7 增大动叶出口马赫数前后涡轮部分气动参数
Table 7. Parts of the aerodynamic parameters of the turbine before and after increasing the outlet Mach number
方案 工况 调节角度/（°） 级效率/% 转子效率/% 导叶总压恢复系数 CASE 1 大流量点 0 91.34 93.68 0.9881 小流量点 −11 81.95 86.25 0.9613 CASE 2 大流量点 0 91.39 93.90 0.9873 小流量点 −14 81.41 86.64 0.9539
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表 8 导叶叶型优化前后涡轮部分气动参数
Table 8. Parts of the aerodynamic parameters of the turbine before and after the optimization of the stator profile
方案 工况 调节角度/（°） 级效率/% 转子效率/% 导叶总压恢复系数 CASE 2 大流量点 0 91.39 93.90 0.9873 小流量点 −14 81.41 86.64 0.9539 CASE 3 大流量点 0 91.49 93.64 0.9890 小流量点 −14 83.35 87.08 0.9667
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表 9 动叶攻角优化前后涡轮部分气动参数
Table 9. Aerodynamic parameters of the turbine before and after the optimization of the blade angle of attack
方案 工况 调节角度/（°） 级效率/% 转子效率/% 动叶相对总压恢复系数 CASE 3 大流量点 0 91.49 93.64 0.9819 小流量点 −14 83.35 87.08 0.9513 CASE 4 大流量点 0 90.80 92.87 0.9780 小流量点 −14 84.72 89.43 0.9787
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表 10 最终优化前后涡轮部分气动参数
Table 10. Parts of aerodynamic parameters of the turbine before and after the final optimization
方案 工况 调节角度/（°） 级效率/% 转子效率/% 导叶总压恢复系数 CASE 0_无间隙 大流量点 0 89.77 91.76 0.9887 小流量点 −11 81.23 85.41 0.9614 CASE 4_无间隙 大流量点 0 90.80 92.87 0.9892 小流量点 −14 84.72 89.43 0.9585 CASE 0_全间隙 大流量点 0 87.47 90.23 0.9834 小流量点 −11 74.23 79.31 0.9494 CASE 4_全间隙 大流量点 0 89.48 92.03 0.9864 小流量点 −14 83.02 88.68 0.9506
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