Review on pressure swirl injector in liquid rocket engine. (April 2018)

• Record Type: Journal Article
• Authors: Kang, Zhongtao; Wang, Zhen-guo; Li, Qinglian; Cheng, Peng
• Is Part Of: Acta astronautica. Volume 145(2018)
• Page Start: 174
• Page End: 198
• Publication Date: 2018-04
• Subjects: Pressure swirl injector -- Liquid rocket engine -- Review; Astronautics -- Periodicals; Outer space -- Exploration -- Periodicals; Astronautics; Periodicals; 629.405
• DOI: 10.1016/j.actaastro.2017.12.038
• Languages: English
• ISSNs: 0094-5765

Abstract

Abstract: The pressure swirl injector with tangential inlet ports is widely used in liquid rocket engine. Commonly, this type of pressure swirl injector consists of tangential inlet ports, a swirl chamber, a converging spin chamber, and a discharge orifice. The atomization of the liquid propellants includes the formation of liquid film, primary breakup and secondary atomization. And the back pressure and temperature in the combustion chamber could have great influence on the atomization of the injector. What's more, when the combustion instability occurs, the pressure oscillation could further affects the atomization process. This paper reviewed the primary atomization and the performance of the pressure swirl injector, which include the formation of the conical liquid film, the breakup and atomization characteristics of the conical liquid film, the effects of the rocket engine environment, and the response of the injector and atomization on the pressure oscillation.