NUMERICAL STUDY OF A 3.5-STAGE AXIAL COMPRESSOR AT ON-AND OFF-DESIGN CONDITIONS
Numerical investigation is conducted on a 3.5-stage axial compressor, on which numerous experimental projects were carried out at the Institute during the last years and an experimental database was established. In the current study five on- and off-design operating points are simulated using a RANS solver and the results are compared with the measurement. The result shows that the compressor performance can be qualitatively predicted by the numerical method. Better agreement is obtained for the on-design operating point. However, as the flow unsteadiness is insufficiently considered, the numerical method produces low-speed flow layers at the end-walls accumulated with the flow passing through the passage, which is in no good agreement with the experimental data. Within the stages the rotor blades receive less work and the difference from the measurement increases with the rotational speed. In contrast, the stator blades increase the static pressure more efficiently. In the computation,the flow in the last stator row tends more to separate on the pressure side of the blade. For the operating points close to the surge line, the separation is more intense than the experimental observation. But for the operating points close to the choke line, the separation is suppressed by the numerical simulation.
Zhuo Wang
Institute of Jet Propulsion and Turbomachinery, RWTH Aachen University, Germany
国际会议
昆明
英文
465-473
2006-09-18（万方平台首次上网日期，不代表论文的发表时间）