跨声速压气机转子流场特性的数值研究  

Numerical Investigation on Flow Field Characteristics of a Transonic Compressor Rotor

作　　者：钟兢军[1] 高宇[1] 李晓东[1] 姜雪红[2] 

机构地区：[1]大连海事大学轮机工程学院,辽宁大连116026 [2]大连交通大学外国语学院,辽宁大连116028

出　　处：《推进技术》2015年第12期1795-1801,共7页Journal of Propulsion Technology

基　　金：国家自然科学基金重点项目(51436002);中央高校基本科研业务费专项资金资助(3132014319)

摘　　要：为研究跨声速压气机转子在设计转速下的内部流场特性,探索其流动机理,考察激波位置及成因,利用三维数值模拟方法对其进行了数值研究。结果表明,该跨声速压气机转子在设计转速下高效工作范围较宽,喘振裕度约为27.15%。近堵塞工况时,转子叶片前缘出现一道脱体的弓形激波,转子叶片流道内也存在一道正激波,激波位置随背压升高向叶片前缘移动;最高效率工况时,叶片前缘叶尖相对马赫数达到1.5。近失速工况时,流道内正激波消失。转子叶顶间隙处存在强烈的激波与附面层及间隙泄漏流的相互作用,该处熵值随背压升高而增大,高熵区随激波前移而向转子叶片前缘移动。In order to investigate the inner flow field characteristics of a transonic compressor rotor at the design speed and explore the flow mechanism,shock wave location and development under the transonic flow condition,the three dimensional numerical analysis are used. The result shows that the transonic compressor rotor has a wide operating ranges,the stall margin is 27.15%. Near choking condition,a bow shock wave occurs on the leading edge of the rotor blade,and a normal shock wave occurs in the flow passage. With the back pressure increasing, the location of shock wave moves forward to the leading edge. The relative Mach number reached by 1.5 at the tip blade on the leading edge in peak efficiency condition. Near stall condition,the normal shock wave disappears. There exists intense interaction between the shock wave- boundary layers and shock wave-tip leakage on the tip of the rotor blade. The entropy increases at that position with the increase of the back pressure. With the shock wave moving forward,the region with high entropy moves towards the leading edge of the blade.

关 键 词：跨声速压气机 流场特性 数值研究 激波 叶顶间隙 

分 类 号：V235.1[航空宇航科学与技术—航空宇航推进理论与工程]