期刊名称：International Journal of Advances in Engineering and Management
电子版ISSN：2395-5252
出版年度：2022
卷号：4
期号：1
页码：1097-1111
DOI：10.35629/5252-0401853860
语种：English
出版社：IJAEM JOURNAL
摘要：This paper presents a preliminary design and simulation for a small combustion chamber designed using SolidWorks. The liquid rocket engine motor is designed as a pressure fed (blowdown) system, and is expected to operate at a chamber pressure of 1MPa, whilst providing a thrust of 2KN, the operating time was designed not to exceed 10s. The expansion ratio of combustion chamber is evaluated at 2.24 with a target combustion efficiency of 95% and nozzle efficiency of between 80-90% all of these corresponded to a specific impulse of (Isp) of 215.15s, while the combustion chamber was designed to utilize a combination of gaseous oxygen (GOX) and Kerosene (C12H26(liq)) as its propellant. The design was intended for a semi static test with steel (AISI 1035 SS) specified as the material for the design. The combustion chamber weighed 6.4132kg with a designed thrust-to-weight ratio on the chamber of 31.8; the maximum resultant displacement was 0.0176436mm with a maximum Von Mises stress of 38.67N/mm2 .
