摘要
将航空发动机整机作为三路来建立模型，用直接积分法分析发动机整机瞬态动力响应。实测发动机安装节处动刚度，以考虑飞机系统的影响，建立了以传递矩阵法为基础的静子主支承刚度阵及主支承到安装节的力一位移传递函数算法，并通过计算转子系统的动力响应来获得整机瞬态动力特性。附有一双转子航空发动机算例，并给出了计算结果。
Both Stephenson et al[3] and Bumer et al[4] pointed out in 1991 that mounting points must be carefully considered in calculating the transient dynamic response of an aeroengine.In 1995 Chinal's Ou et al[5] gave mounting points such consideration through empirical experience and making some assumptions. We now measure experimentally the dynamic characteristics of mounting points placed alone (without aeroengine) on an aircraft in order to make calculation of transient response of aeroengine closer to reality.In addition to realitic consideration of mounting points, we make some improvement in method of calculation. TMM (Transfer MatriX Method) has been successfully applied to rotor (including both inner and outer rotor) calculations. We now extend it to stator calculation. Thus, we not only conveniently use one method (TMM ) but also, more importantly,we reduce the number of degrees of freedom and computation time as compared with conventional stator calculation method.Eqs. (3) and (4) give respectively the transient precession speed and precession acceleration of rotor.Finally a certain type of double-spool aeroengine is taken as example. The results calculated with our extended TMM method agree well with test data. Of course, the dynamic characteristics of mounting points placed alone on the test setup are measured.
出处
《西北工业大学学报》
EI
CAS
CSCD
北大核心
1996年第2期234-238,共5页
Journal of Northwestern Polytechnical University
关键词
振动
瞬态响应
航空发动机
转子-机匣系统
aeroengine, transient response, mounting point, TMM (transfer matrix method)
