多级轴流压气机多排可转导/静叶联合调节规律研究

推进技术 ›› 2017, Vol. 38 ›› Issue (2): 334-340.

多级轴流压气机多排可转导/静叶联合调节规律研究

廖吉香,姜斌,吕从鹏,郑群,邱毅,王国强

哈尔滨工程大学动力与能源工程学院，黑龙江哈尔滨 150001,哈尔滨工程大学动力与能源工程学院，黑龙江哈尔滨 150001,哈尔滨工程大学动力与能源工程学院，黑龙江哈尔滨 150001,哈尔滨工程大学动力与能源工程学院，黑龙江哈尔滨 150001,哈尔滨工程大学动力与能源工程学院，黑龙江哈尔滨 150001,哈尔滨工程大学动力与能源工程学院，黑龙江哈尔滨 150001

发布日期:2021-08-15
作者简介:廖吉香，女，博士生，研究领域为叶轮机械气动热力学。
基金资助:
国家自然科学基金(51476039)；中央高校基本科研业务专项基金(HEUCF150304)。

Numerical Optimization of Combined Adjustment of Multi-Row Variable Inlet Guide Vane and Stators in a Multistage Axial-Flow Compressor

College of Power and Energy Engineering，Harbin Engineering University，Harbin 150001，China,College of Power and Energy Engineering，Harbin Engineering University，Harbin 150001，China,College of Power and Energy Engineering，Harbin Engineering University，Harbin 150001，China,College of Power and Energy Engineering，Harbin Engineering University，Harbin 150001，China,College of Power and Energy Engineering，Harbin Engineering University，Harbin 150001，China and College of Power and Energy Engineering，Harbin Engineering University，Harbin 150001，China

Published:2021-08-15

摘要/Abstract

摘要： 为了减少多级轴流压气机多排可转导/静叶联合调节对实验的依赖，利用Isight软件、HARIKA算法以及部分自编接口程序搭建可转导/静叶联合调节方案的优化设计平台。通过结合压气机原特性给定目标喘振边界并量化当前喘振边界与目标喘振边界的距离作为目标函数，从而便于快速获取压气机不同转速下多排可转导/静叶安装角的调节角度，实现压气机可转导/静叶的无级调节。并将此优化平台应用于八级轴流压气机，发现可转导/静叶的调节能力受限于调节级数，需仔细考虑所需的调节级数以达到预期的调节目标。优化后压气机非设计转速的喘振边界向左上方移动，如Case 2中70%转速时近失速点流量减小了17.94%，近失速点压比增加了4.93%，压气机的低工况稳定性得到改善。利用三维软件计算优化后的压气机特性，证明了此优化平台的可行性和有效性。

关键词: 可转导叶；可转静叶；HARIKA算法；优化设计；喘振边界

Abstract: In order to reduce the dependence on experiments in the combined adjustment of multi-row variable inlet guide vane and stators in a multistage axial-flow compressor，an optimization design platform was constructed by Isight software，HARIKA algorithm and some self-compiled interface programs. This optimization design platform quantified the distances between the original surge margin boundary line and the objective surge margin boundary line as an objective function，which is given according to the original characteristic lines of compressor，so the adjustive angles of inlet guide vane and stators are easily obtained at the diffierent rotating speed to realize the stepless adjustment. This platform was used in a eight-stage axial-flow compressor，the results show that the ability to regulate the inlet guide vane and the stators is limited by the number of adjustive rows of blades，so it need to balance the number of adjustive rows of blades to achieve the desired goal. The surge margin of the compressor moves up and left greatly at the off-design speed after optimization，for example，the mass flow reduces by 17.94% and pressure ratio increases by 4.93% near stall point at 70% rotating speed in Case 2，so the aerodynamic stability of compressor is improved at the low rotating speed. Finally，the setting angles of inlet guide vane and stators obtained from one-dimensional optimization are substituted in 3-D software to compute the characteristic lines of compressor，the results demonstrate the feasibility and effectiveness of the optimization design platform.

Key words: Variable inlet guide vane； Variable stators； HARIKA algorithm； Optimization design； Surge margin boundary

廖吉香,姜斌,吕从鹏,郑群,邱毅,王国强. 多级轴流压气机多排可转导/静叶联合调节规律研究[J]. 推进技术, 2017, 38(2): 334-340.

LIAO Ji-xiang,JIANG Bin,LV Cong-peng,ZHENG Qun,QIU Yi,WANG Guo-qiang. Numerical Optimization of Combined Adjustment of Multi-Row Variable Inlet Guide Vane and Stators in a Multistage Axial-Flow Compressor[J]. Journal of Propulsion Technology, 2017, 38(2): 334-340.

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