摘要
对转桨扇开式转子发动机性能计算的难点在于对转桨扇部件的性能计算。传统方法是将对转桨扇简化处理为涡轮螺桨进行计算,但精度较低。本文基于传统涡轮螺桨性能模拟方法,考虑前排桨扇出口气流对后排桨扇的影响,对前、后排桨扇进行独立建模,建立了开式转子发动机对转桨扇部件级性能计算模型,并使用美国NASA风洞试验数据进行验证。结果表明,对转桨扇性能模型计算精度较高,采用此模型可较准确地模拟不同设计参数和不同控制规律下的对转桨扇性能,并评估其对开式转子发动机总体性能的影响。
The prop-fan performance calculation is the most difficult part of the performance prediction of open rotor engine with counter-rotating prop-fan. To simplify a prop-fan as a propeller is a usually used method which is not so precise. Based on the traditional method, considering the influence of outlet airflow from the front blades on the rear blades, the front model and rear model were built separately. Then the open rotor engine counter-rotating prop-fan component performance model was established and demonstrat- ed by wind tunnel test data from NASA. The counter-rotating prop-fan model was proved to be precise. With this model, various design parameters and different performance under control laws could be precisely simulated, and its influence on the overall performance of open rotor engine could be evaluated.
出处
《燃气涡轮试验与研究》
北大核心
2012年第1期20-24,共5页
Gas Turbine Experiment and Research
关键词
民用航空发动机
开式转子
对转桨扇
气动特性
性能建模
civil aero-engine
open rotor
counter-rotating prop-fan
aerodynamic performance
performance modeling
