跨音速涡轮平面叶栅气动性能试验研究  

Experimental investigation of aerodynamic parameters in transonic turbine linear cascade

作　　者：刘壮[1] 阚晓旭[2] 陆华伟[2] 钟兢军[2] 

机构地区：[1]中航工业沈阳发动机设计研究所,沈阳110015 [2]大连海事大学轮机工程学院,辽宁大连116026

出　　处：《大连海事大学学报》2013年第2期123-127,共5页Journal of Dalian Maritime University

摘　　要：为研究某型涡轮叶片根部截面的平面叶栅在不同攻角和不同马赫数下的气动性能,采用风洞吹风试验对叶栅总损失特性、出口能量损失分布、叶片表面和壁面压力与马赫数分布等气动参数变化情况进行分析.结果表明,叶栅所采用的叶型具有较为明显的后部加载特性,叶栅能量损失在较宽攻角范围内保持较低水平,且随着出口等熵马赫数的变化呈现先减小后增大的变化规律.The performance of turbine linear cascades with differ- ent incidences and Mach numbers is studied experimentally. The aerodynamic parameters such as the total energy loss, the distri- bution of energy loss at the exit of cascade, the distribution of pressure at blade surface and endwall as well as Mach number distribution are discussed by wind tunnel. Results show that this blade has obvious characteristic of the aft-loading. The energy losses in the entire range of incidences are low , and the energy loss decreases first and then increases.

关 键 词：涡轮平面叶栅 气动性能 试验研究 能量损失 后部加载 

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]