基于时间推进通流反问题的跨声速轴流风扇设计研究

李进广; 吴虎; 杨晨

doi:10.13224/j.cnki.jasp.20250033

基于时间推进通流反问题的跨声速轴流风扇设计研究

doi: 10.13224/j.cnki.jasp.20250033

李进广^1,,
吴虎^1,*, ,,
杨晨²

1.
西北工业大学动力与能源学院，西安 710072
2.
大连理工大学能源与动力学院，辽宁大连 116024

基金项目: 航空科学基金（2024Z039063002）

详细信息

作者简介:
李进广（1995-），男，博士生，主要从事叶轮机械气动热力学研究。 E-mail：lijinguang078@mail.nwpu.edu.cn

通讯作者:
吴虎（1963-），男，教授，博士，主要从事叶轮机械气动热力学及航空发动机总体设计研究。E-mail：wuhu@nwpu.edu.cn

中图分类号: V231.3
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- 被引次数: 0
出版历程
- 收稿日期: 2025-01-17
- 网络出版日期: 2025-05-31

Study on design of transonic axial-flow fans based on time-marching throughflow inverse design method

LI Jinguang^1
,,
WU Hu^{1,*
, ,},
YANG Chen²

1.
School of Power and Energy，Northwestern Polytechnical University，Xi’an 710072，China
2.
School of Energy and Power Engineering，Dalian University of Technology，Dalian Liaoning 116024，China

摘要

摘要:
基于计算流体力学（CFD）理论，发展了一种面向多级轴流风扇的通流反设计方法。为准确加载无黏叶片力，基于近似因子分解法提出了一种鲁棒的流面几何更新数值解法。采用该方法对一款两级跨声速风扇进行了重新设计，并通过全三维数值模拟进行了验证。结果显示：程序能够稳健且高效地实现通流设计的完全收敛，且子午流场与全三维周向平均结果基本吻合。经全三维验证，设计工况的质量流量和总压比均达到设计目标；非设计工况下本设计方案与其原型性能各有优劣。非设计转速下的峰值效率虽有所降低（最大降低1.04%），但稳定裕度和失速总压比均有一定提升（最大分别提升1.7%和1.26%）。
- 反问题 /
- 轴流风扇 /
- 时间推进 /
- 通流方法 /
- 气动设计
Abstract:
A throughflow inverse design method for multi-stage axial-flow fans was developed based on computational fluid dynamics (CFD) theory. A robust numerical method was proposed based on the approximate factorization method to impose the inviscid blade force on the blades accurately. The process was applied to the redesign of a two-stage transonic fan, and the design was validated through full three-dimensional numerical simulations. The results showed that the program can robustly and efficiently achieve complete convergence of the throughflow design, with the meridional flow fields in good agreement with the three-dimensional circumferentially averaged results. Through full three-dimensional simulation validations, the present design results achieved the target mass flow rate and total pressure ratio under the design point. At off-design operations, the current configuration demonstrated complementary advantages compared with the prototype: While peak efficiency experienced slight reductions at off-design rotational speeds (with a maximum reduction of 1.04%), the stability margin and stall pressure ratio showed maximum improvements of 1.7% and 1.26%, respectively.
- inverse problem /
- axial-flow fans /
- time-marching /
- throughflow method /
- aerodynamic design

HTML

图 1 两级风扇中径处环量分布示意图

Figure 1. Schematic diagram of circulation distribution at meanline of a two-stage fan

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图 2 流面相切方程残差收敛史

Figure 2. Convergence history of surface-flow slip equation

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图 3 流面几何包角等值线分布云图

Figure 3. Contours of wrap angle on flow surface

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图 4 大折转角算例的流面几何

Figure 4. Flow surface geometry for high-turning-angle test case

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图 5 时间推进通流反问题求解流程图

Figure 5. Flowchart of time-marching throughflow inverse problem solution

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图 6 两级风扇通流计算网格

Figure 6. Meridional grid for two-stage fan throughflow design

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图 7 平均残差及流量收敛史

Figure 7. Convergence history of average residuals and mass flow rate

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图 8 各叶片排尾缘处环量沿展向分布对比

Figure 8. Comparison of trailing-edge circulation distribution along spanwise direction for all blade rows

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图 9 各叶片排总压损失系数沿展向分布

Figure 9. Spanwise distribution of total pressure loss coefficient for all blade rows

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图 10 转子前、尾缘相对气流角沿展向分布

Figure 10. Spanwise distribution of relative flow angle at rotor leading edge and trailing edge

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图 11 静子前、尾缘绝对气流角沿展向分布

Figure 11. Spanwise distribution of absolute flow angle at stator leading edge and trailing edge

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图 12 冲角设计结果

Figure 12. Design results of the incidence angle

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图 13 落后角设计结果

Figure 13. Design results of the deviation angle

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图 14 第一级转子的最小喉道面积比

Figure 14. Minimum throat area ratio of the first-stage rotor

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图 15 第二级转子的最小喉道面积比

Figure 15. Minimum throat area ratio of the second-stage rotor

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图 16 三维数值仿真网格效果图

Figure 16. 3D computational mesh visualization

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图 17 CFX与通流设计结果扩散因子对比图

Figure 17. Comparison of diffusion factor between CFX and throughflow design results

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图 18 CFX与通流设计结果总压损失系数对比图

Figure 18. Comparison of total pressure loss coefficient between CFX and throughflow design results

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图 19 不同展向位置的相对马赫数等值线分布云图

Figure 19. Contours of relative Mach number for different spanwise locations

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图 20 子午流道相对马赫数等值线分布云图

Figure 20. Meridional contours of relative Mach number

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图 21 总压比-流量特性曲线

Figure 21. Total pressure ratio-mass flow rate performance curves

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图 22 等熵效率-流量特性曲线

Figure 22. Isentropic efficiency-mass flow rate performance curves

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表 1 通流设计所采用的总压损失模型

Table 1. Total pressure loss model employed in throughflow design

模型类别	关系式来源
最小损失	Lieblein等^[23-24]
二次流损失	Howell^[25]
端壁损失	Howell^[25]
激波损失	Carmody和Creveling^[26]

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表 2 两级风扇主要设计参数^[27-28]

Table 2. Primary design variables of two-stage fan^[27-28]

参数	数值
总压比	2.80
等熵效率/%	83.90
换算流量/（kg/s）	83.5
最大叶尖线速度/（m/s）	441.96
设计转速/（r/min）	10720
展弦比	2.02，2.19，2.50，1.98

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表 3 本方法与NASA报告中的总体性能参数对比

Table 3. Comparison of overall performance parameters between present method and NASA report

参数	数值
参数	NASA	反问题
流量/（kg/s）	83.500	83.508
等熵效率/%	83.90	86.11
总压比	2.80	2.88

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表 4 网格参数及CFX求解器的数值格式设置

Table 4. Mesh parameters and numerical scheme configuration in CFX solver

参数	数值或说明
B2B拓扑	O4H
总网格量/10⁴	368.2
第1层网格高度/10⁻⁶ m	5
转子叶尖间隙/mm	0.4
湍流模型	SST（shear stress transport）
对流项格式	高精度

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表 5 CFX与通流设计结果的总体性能参数对比

Table 5. Comparison of overall performance parameters between CFX and throughflow design results

参数	数值		偏差值/%
参数	CFX	通流反问题	偏差值/%
总压比	2.88	2.88
流量/（kg/s）	84.663	83.508	+1.38
等熵效率/%	83.58	86.11	−2.53

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表 6 两种设计方案的稳定裕度、峰值效率和失速总压比对比

Table 6. Comparison of stability margin, peak efficiency and stall pressure ratio between two design results

转速	设计方案	稳定裕度/%	峰值效率/%	失速总压比
100% 设计转速	NASA	16.4	85.96	3.23
	本设计	17.7	86.37	3.27
	性能增益/%	+1.3	+0.41	+1.24
85% 设计转速	NASA	11.3	90.51	2.39
	本设计	12.5	90.02	2.42
	性能增益/%	+1.2	−0.49	+1.26
70% 设计转速	NASA	8.9	88.24	1.79
	本设计	10.6	87.20	1.80
	性能增益/%	+1.7	−1.04	+0.56

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