Characterization of a Kerosene-derived Rocket Fuel
عنوان مقاله: Characterization of a Kerosene-derived Rocket Fuel
شناسه ملی مقاله: ICHEC05_417
منتشر شده در پنجمین کنگره بین المللی مهندسی شیمی در سال 1386
شناسه ملی مقاله: ICHEC05_417
منتشر شده در پنجمین کنگره بین المللی مهندسی شیمی در سال 1386
مشخصات نویسندگان مقاله:
Reza Ghiai - Iranian Aerospace Organization, Tehran, Iran
Davood Heydari - Iranian Aerospace Organization, Tehran, Iran
خلاصه مقاله:
Reza Ghiai - Iranian Aerospace Organization, Tehran, Iran
Davood Heydari - Iranian Aerospace Organization, Tehran, Iran
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.
کلمات کلیدی: Rocket Fuel; Hydrocarbon; kerosene; Thermophysics; Combustion
صفحه اختصاصی مقاله و دریافت فایل کامل: https://civilica.com/doc/46267/