文章基本信息

标题：Design of a 2kn Liquid Fuel Rocket Engine Propellant Injector Part 2
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作者：Abdulkadir A.Bage ; Abdulrahman Abdulazeez ; Olusegun S.Sholiyi 等
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：3
页码：829-842
DOI：10.35629/5252-0403616624
语种：English
出版社：IJAEM JOURNAL
摘要：This paper presents a preliminary design for a small propellant injector designed using SolidWorks. The propellant injector is designed for a pressure fed (blow-down) system, and is expected to operate at a chamber pressure of 1MPa, whilst providing a thrust of 2KN, the operating time is designed not to exceed 20s. A spray nozzle orientation type was selected for this design with a target combustion efficiency of 95% and nozzle efficiency of between 80-90%, all of these corresponded to a specific impulse (Isp) of 216.16s, while the propellant injector was designed to utilize a combination of gaseous oxygen (GOX) and Kerosene (C12H26(liq)) as its propellant. The design is intended for a semi static test with steel (AISI 1035 SS) specified as the material for the design. The propellant injector weighed 3.96208kg. The Danfoss oil nozzle type OD was considered as the spray nozzle option for the injector design. The oil nozzle is to be used to atomize the fuel (kerosene) and oxidizer (oxygen) at high pressures; and because it was crucial to avoid scrubbing of the chamber wall by high-temperature oxidizing streams, a cooling bias due to maldistribution was proposed, and since the Danfoss nozzle had suitable atomization capacities the size and weight of pressure vessels would be minimized. It is also important to note that the injector implementation in liquid rocket engines; determines the percentage of the theoretical performance that the nozzle can achieve.
关键词：Liquid fuel rocket engine;Propellant injector