总压畸变对超声速压气机动叶端区流场结构的影响

Effects of Total Pressure Distortion on Rotor End Wall Flow Structure of a Supersonic Compressor

关键词:  总压畸变  数值模拟  压气机  动叶  端区 

Key words:  Total pressure distortion  Numerical simulation  Compressor  Rotor  End wall

摘要:

采用全周非定常数值模拟方法,对两种畸变进口条件下的超声速压气机流场进行求解,了解动叶流场参数变化和气动性能与畸变来流条件的关系,重点分析动叶根部和顶部附近激波位置、结构和强度的变化情况,揭示动叶流场参数的动态变化规律。研究表明,随畸变区范围增加,压气机质量流量和效率下降；动叶流场参数对畸变来流的动态响应主要表现为激波位置、结构和强度的周期变化,当畸变区范围足够大时,流道在畸变区中会经历深度畸变；27.2%畸变时,畸变区内流道存在根部和顶部流动状态不一致的时刻,流场状态复杂。38.2%畸变时,畸变区内动叶叶顶和叶根区域都能达到深度畸变状态,流动损失较大且稳定性差。 

Abstract:

In order to analyze the response of flow parameters in rotor to the distorted inlet conditions, full annuls unsteady numerical simulation was carried out to study a supersonic compressor rotor flow field with two kinds of distorted inlets. Position, structure and intensity of shock wave near end walls were analyzed in detail. Study shows that the compressor mass flow rate and efficiency will decrease as distorted area increases. Distorted flow impact on rotor flow field is mainly reflected in the influence on shock wave structure, position and intensity. If the distorted region is large enough, deep distortion will be induced in rotor passages. The flow fields in rotor hub and casing area are not coincident in distorted region with 27.2% distortion.The flow field in rotor is even more complex and the flow fields are both even more deeply distorted with 38.2% distortion. 