سال انتشار: ۱۳۸۶

محل انتشار: پنجمین کنگره بین المللی مهندسی شیمی

تعداد صفحات: ۱۰

نویسنده(ها):

Reza Ghiai – Iranian Aerospace Organization, Tehran, Iran
Davood Heydari – Iranian Aerospace Organization, Tehran, Iran

چکیده:

One-formula surrogate fuel formulation is developed to support the design of injectors and thrust chambers of kerosene-fueled rocket engines. This surrogate fuel model depicts a fuel blend that properly represents the general physical and chemical properties of rocket fuel (RF). The accompanying gaseous-phase thermodynamics of the surrogate fuel is anchored with the heat of formation of RF and verified by comparing a series of rocket thrust chamber calculations. The final thermophysics formulations are incorporated with a computational model for prediction of the combustor efficiency of a bi-propellant combustor. The model predictions agreed reasonably well with those of the tests.