سال انتشار: ۱۳۸۶

محل انتشار: هفتمین همایش انجمن هوافضای ایران

تعداد صفحات: ۵

نویسنده(ها):

M. Ziabasharhagh – Assistant, Department of Mechanical Engineering, khaje nasir Technology University, Tehran-Iran
M. Mohammadi – M.S Student, Department of Mechanical Engineering, khaje nasir Technology University, Tehran-Iran
M. Madandar Arani – Aerospace organization, M.S of mechanical engineering

چکیده:

In this paper, a fuel-rich gas generator of open cycle turbopump System and its optimization was experimentally tested. The propellant that was used in this test is Kerosene/ 3 2 4 HNO + N O . The base designing of gas generator is determined by optimization technique. The objective function in this paper is work ability of gas generator over its weight. As a result, global optimization method by genetic algorithm can prepare the result of optimization without any consideration to initial condition. Sensitivity analyses could evaluate the design variables effect on the objective function respectively and relative dependence could be found. Also another sensitivity analyses for basic parameters of genetic algorithm that have intense effect, was evaluated. In present study effect of parameters like o/f ratio, combustion chamber pressure was tested. Also the turbulence ring was found dominantly effective in enhancing the mixing of burned gas in radial direction. The results show that as operative pressure and o/f ratio reach to 50 bars and 0.6 respectively. The objective function is achieved to the global optimum point in those conditions.