1+1/2对转涡轮气动设计及变工况分析

张超炜; 王涛; 迟根

doi:10.13224/j.cnki.jasp.20240266

1+1/2对转涡轮气动设计及变工况分析

doi: 10.13224/j.cnki.jasp.20240266

1.
上海理工大学能源与动力工程学院，上海 200082
2.
合肥工业大学汽车与交通工程学院，合肥 230009

详细信息

作者简介:
张超炜（1992-），男，讲师、硕士生导师，博士，主要从事叶轮机械气动热力学研究。E-mail：zhangchaowei@usst.edu.cn

中图分类号: V211.3
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出版历程
- 收稿日期: 2024-04-28
- 网络出版日期: 2025-09-10

Aerodynamics design and off-design condition analysis of 1+1/2 counter-rotating turbine

1.
School of Energy and Power Engineering，University of Shanghai for Science and Technology，Shanghai 200082，China
2.
School of Automotive and Transportation Engineering，Hefei University of Technology，Hefei 230009，China

摘要

摘要:
与常规涡轮相比，对转涡轮具有效率高、质量轻和陀螺力矩小的优点，已广泛应用于军用和民用航空发动机。开展1+1/2对转涡轮三维气动设计，并进行数值计算，结果表明：在设计工况下，对转涡轮质量流量为4.13 kg/s，总体膨胀比为5.823，高压涡轮膨胀比达到2.641，低压涡轮膨胀比达到2.205，总体等熵效率为88.70%，总输出功率为1815.2 kW，基本满足设计要求。对对转涡轮设计点进行流动损失分析，发现高压涡轮动叶尾缘燕尾形激波强度在50%叶高处最高，并向叶根和叶顶区域逐渐减弱，且低压涡轮进口压力面存在少量流动分离。对对转涡轮进行变工况分析，发现随着对转涡轮总膨胀比的增加，高低压涡轮动叶尾缘激波强度均逐渐增大，低压涡轮动叶进口流动分离减弱，高压涡轮等熵效率有所减小，低压涡轮和对转涡轮整体等熵效率均先增加后基本不变。随着低压涡轮转速的提高，对转涡轮质量流量几乎不变，整体等熵效率先增加后减小，输出功率逐渐增加。
- 无导叶对转涡轮 /
- 气动设计 /
- 变工况 /
- 膨胀比 /
- 激波
Abstract:
Compared with the conventional turbines, counter-rotating turbines have the advantages of high efficiency, light weight and small gyroscopic torque, and have been widely used in military and civil aviation engines. The 3D aerodynamics design of 1+1/2 vaneless counter-rotating turbine (VCRT) was carried out by commercial software, and numerical simulation was completed. The results showed that when the mass flow rate was 4.13 kg/s, the overall expansion ratio was 5.823. The high pressure turbine (HPT) expansion ratio was 2.641, and the low pressure turbine (LPT) expansion ratio reached 2.205. The VCRT isentropy efficiency was 88.70%, and the total output power was 1815.2 kW, which met the design requirements. The flow loss analysis of the VCRT at the design condition showed that the intensity of the dovetail shock wave at the trailing edge of HPT rotor was the highest at the 50% span, and gradually weakened to the root and tip of the blade. There was a little flow separation on the pressure surface of the LPT inlet. Moreover, the off-design conditions of the 1+1/2 counter-rotating turbine were analyzed. It was found that with the increase of the VCRT expansion ratio, the intensity of shock wave at the trailing edge of the HPT rotor gradually increased, and the flow separation of LPT was weakened. Therefore, the isentropic efficiency of HPT decreased, and the overall isentropic efficiency and LPT isentropic efficiency increased first and then kept unchanged. With the increase of the LPT rotational speed, the mass flow rate of VCRT was almost constant, the overall isentropic efficiency increased first and then decreased, and the output power increased gradually.
- vaneless counter-rotating turbine /
- aerodynamic design /
- off-design condition /
- expansion ratio /
- shock wave

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图 1 1+1/2对转涡轮子午流道示意图

Figure 1. Schematic of 1+1/2 VCRT meridional passage

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图 2 高压涡轮导叶叶片角分布

Figure 2. Guide vane blade angle distribution of HPT

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图 3 高压涡轮导叶叶片厚度分布

Figure 3. Guide vane blade thickness distribution of HPT

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图 4 高压涡轮动叶叶片角分布

Figure 4. Rotor blade angle distribution of HPT

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图 5 高压涡轮动叶叶片厚度分布

Figure 5. Rotor blade thickness distribution of HPT

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图 6 高压涡轮三维几何模型

Figure 6. HPT 3D geometrical model

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图 7 低压涡轮动叶叶片角分布

Figure 7. Rotor blade angle distribution of LPT

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图 8 低压涡轮动叶叶片厚度分布

Figure 8. Rotor blade thickness distribution of LPT

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图 9 低压涡轮三维几何模型

Figure 9. LPT 3D geometrical model

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图 10 1+1/2对转涡轮三维几何模型

Figure 10. 1+1/2 VCRT 3D geometrical model

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图 11 1+1/2对转涡轮网格

Figure 11. 1+1/2 VCRT mesh

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图 12 1+1/2对转涡轮三维性能预测结果

Figure 12. 1+1/2 VCRT 3D predicted performance

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图 13 1+1/2对转涡轮设计点子午面相对马赫数分布

Figure 13. 1+1/2 VCRT relative Mach number distribution in meridional plane at the design condition

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图 14 1+1/2对转涡轮设计点B2B面相对马赫数分布

Figure 14. 1+1/2 VCRT relative Mach number distribution in B2B plane at the design condition

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图 15 1+1/2对转涡轮设计点B2B面相对速度流线分布

Figure 15. 1+1/2 VCRT relative velocity streamline distribution in B2B plane at the design condition

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图 16 设计点高压涡轮动叶子午面出口相对马赫数沿展向分布

Figure 16. Relative Mach number distribution along spanwise at HPT meridional plane outlet at the design condition

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图 17 低压涡轮设计点动叶出口绝对马赫数分布

Figure 17. Absolute Mach number distribution at LPT outlet at the design condition

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图 18 三排叶片设计点不同叶高静压载荷分布

Figure 18. Static pressure load distribution of three rows at the design condition

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图 19 不同VCRT总膨胀比下高低压涡轮总体性能变化

Figure 19. HPT and LPT performance varying with VCRT expansion ratio

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图 20 不同VCRT总膨胀比下1+1/2对转涡轮B2B面相对马赫数分布

Figure 20. VCRT relative Mach number distribution in the B2B plane with different VCRT expansion ratios

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图 21 不同VCRT总膨胀比下高压涡轮动叶子午面出口相对马赫数沿展向分布

Figure 21. Relative Mach number distribution along spanwise at HPT meridional plane outlet with different VCRT expansion ratios

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图 22 不同VCRT总膨胀比下三排叶片静压载荷分布

Figure 22. Static pressure load distribution of three rows with different VCRT expansion ratios

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图 23 不同低压涡轮转速下高低压涡轮总体性能变化

Figure 23. HPT and LPT performance varying with LPT rotational speed

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图 24 不同低压涡轮转速下1+1/2对转涡轮50%叶高相对马赫数分布

Figure 24. VCRT relative Mach number distribution in the 50% span with different LPT rotational speeds

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图 25 不同低压涡轮转速下高压涡轮动叶子午面出口相对马赫数沿展向分布

Figure 25. Relative Mach number distribution along spanwise at HPT meridional plane outlet with different LPT rotational speeds

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表 1 高压涡轮设计参数

Table 1. HPT design parameters

参数	数值
参数	导叶	动叶
进口叶尖直径/mm	317.2	319.6
进口轮毂直径/mm	285.8	282.9
进口叶尖叶片角/（°）	5	−26
进口轮毂叶片角/（°）	5	−35
出口叶尖直径/mm	317.8	328
出口轮毂直径/mm	285	273.2
出口叶尖叶片角/（°）	−69	76
出口轮毂叶片角/（°）	−67	71
叶片数	53	41

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表 2 低压涡轮设计参数

Table 2. LPT design parameters

参数	数值	参数	数值
进口叶尖直径/mm	332.8	出口轮毂直径/mm	247.2
进口轮毂直径/mm	267	出口叶尖叶片角/（°）	−75
进口叶尖叶片角/（°）	26	出口轮毂叶片角/（°）	−65
进口轮毂叶片角/（°）	40	叶片数	59
出口叶尖直径/mm	350.2

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表 3 数值结果与试验值对比

Table 3. Comparison of CFD result with experiment

参数	试验值	数值结果	相对误差/%
膨胀比	2.25	2.311	2.71
出口马赫数	0.34	0.348	2.35
等熵效率/%	92.5	92.0	0.54

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