脉冲爆震燃烧室与涡轮相互作用的试验  

Experimental investigations of interaction of a pulse detonation combustor with a turbine

作　　者：邓君香[1] 郑龙席[1] 严传俊[1] 蒋联友[1] 李娜[1] 熊姹[1] 

机构地区：[1]西北工业大学动力与能源学院,西安710072

出　　处：《航空动力学报》2009年第2期307-312,共6页Journal of Aerospace Power

基　　金：国家自然科学基金(50336030)

摘　　要：采用汽油和空气作为燃料和氧化剂,进行了脉冲爆震燃烧室(PDC)与涡轮相互作用的原理性模型试验装置的试验.试验结果表明:PDC工作平稳,在发动机爆震工作时压气机出口空气质量流量比用于PDC产生爆震的空气质量流量大100 kg/h左右;在PDC出口前已形成充分发展的爆震波,压力波经过涡轮膨胀后峰值压力和波速明显降低;且充填系数越大,各位置处的平均峰值压力越高,压力波经过涡轮后的衰减越小;涡轮在经受累计40多分钟共12 000多次脉冲爆震波或压力波的冲击后仍然完好无损.Experimental investigations of a principle model of interaction of pulse detonation combustor （PDC） with turbine were made by using gasoline and air as fuel and oxidizer. The experimental results show that pulse detonation combustor can run stably. During PDC detonating, the air mass flow at the compressor outlet is about 100 kg/h more than that of PDC required for detonation. The full pulse detonation is achieved before the PDC outlet. The peak pressure and wave speed of pressure wave are significantly reduced after expansion through the turbine. Larger fill fraction can lead to a stronger detonation wave and a strong shock wave can be less affected by an obstacle like a turbine than a weak one. The turbocharger does not exhibit any signs of damage after over 40 minutes of detonation testing.

关 键 词：脉冲爆震燃烧室(PDC) 涡轮 相互作用 试验研究 

分 类 号：V231.2[航空宇航科学与技术—航空宇航推进理论与工程]