摘要
本文重点介绍采用基元叶栅法并用完全径向平衡方程描述压气机子午面内流动的计算多级轴流压气机非设计点性能以及径向畸变影响的模型。该模型考虑了变比热的影响 ,并根据计算求得的基准总压损失和非基准总压损失之和确定压气机的滞止绝热效率。所用数据适用于扩散因子大于 0小于 1 ,而马赫数在 0到1 .6之间的情况。压气机的加功量或增压比由其基元叶栅的落后角确定。该模型允许指定每一叶排的进口流量 ,亦即允许在两叶排之间有流量旁路。本文还着重分析了 RB-1 99高压压气机的特性 ,预测结果与实验数据吻合很好。
A model to calculate axial flow compressor off design performance with uniform and radial distorted inlet flow is proposed,which takes into account variable specific heat and full radial equilibrium of the flow,including streamline curvature and radial gradients of total enthalpy and entropy.The efficiency is determined from a total pressure loss coefficient which is taken as the sum of a calculated reference loss coefficient and an off reference increment in loss coefficient.The correlated data are used for diffusion factors from 0 to 1 0 and Mach numbers from 0 to 1 6.The compression work or the total pressure ratio of a compressor is determined through the use of cascade element performance data concerning deviation angle.The model allows user to specify the mass flow at each blade row i.e.allows existence of flow bypass between two blade rows.Results for a five stage high speed compressor are analyzed in detail,and the comparison with the experimental data demonstrates that the model is reliable.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2000年第3期225-228,共4页
Journal of Aerospace Power
