动叶优化对跨声速压气机级性能影响的数值研究  

Numerical Study on the Impact of Optimized Rotor on the Performance of a Transonic Compressor Stage

作　　者：李晓东[1] 钟兢军[1] 高宇[1] 

机构地区：[1]大连海事大学轮机工程学院,大连116026

出　　处：《科学技术与工程》2018年第1期145-152,共8页Science Technology and Engineering

基　　金：国家自然科学基金重点资助项目(51436002);辽宁省高等学校创新团队项目(LT2015004);中央高校基本科研业务费专项资金资助

摘　　要：为研究动叶优化对于整级性能的影响,用优化动叶代替原型动叶在0.8~1.1倍设计转速进行了数值研究。结果显示,动叶优化后整级的通流能力得到提升,设计转速下堵塞流量较原型提升了0.53%;级性能得到了提高,在1.0倍和1.1倍设计转速时最高效率分别提升了0.45%、0.44%。0.8~0.9倍设计转速时,压比和效率变化不明显;动叶流道内激波结构变化不明显,叶顶和叶根的激波强度有所增加,中径处激波强度降低;动叶优化后,静叶叶顶区域进口气流角明显增大,恶化了静叶叶顶吸力面的流动状态,导致静叶吸力面叶顶分离区增大,静叶出口总压损失系数增加。To investigate the influence of an optimized rotor on transonic stage,numerical study on 0. 8 ~1. 1 times of design rotational speed is conducted,during which,the original rotor is replaced by the optimized one. Results show that,with the optimized rotor,the transonic stage has a higher mass flow rate,the mass flow rate at near chock point is improved by 0. 53% relatively. The stage characteristic has been improved,the optimum adiabatic efficiency is improved by 0. 45% and 0. 44% relatively at 1. 0 and 1. 1 times of design rotational speed. However,the adiabatic efficiency and total pressure ratio improve little at 0. 8 ~ 0. 9 times of design rotational speed. The structure of shock inside the rotor passage changes little,in the hub and tip region the shock has been strengthened and in the mid-span region been weakened. With an optimized rotor,the inlet flow angel in tip region of the stator increases significantly,makes the flow state worse in the tip region of suction side,leads to a larger separation in the tip region of suction side,and eventually increases the total pressure loss coefficient at the outlet of stator.

关 键 词：动叶优化 跨声速级 变转速 数值研究 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]