Volume 11, 2019Progress in Propulsion Physics – Volume 11
|Page(s)||161 - 176|
|Published online||08 February 2019|
Analytical viscous flow model and test validation of a swirl injector for rocket engine application
Università di Pisa 8 Via Caruso, Pisa 56122, Italy
2 Technische Universität Dresden 32 Marschnerstrasse, Dresden 01307, Germany
The generally adopted flow model inside a swirl injector, widely used injection concept for propulsive applications, relies upon the hypothesis of ideal flow neglecting the fluid viscosity effects. This model showed significant prediction errors with relatively high viscosity propellants, often leading to the need of an experimental characterization of the injection elements. In this paper, an analytical approach is presented, which includes the effects of viscous diffusion on the injector performance leading to a close form flow solution. The built model is thus experimentally validated testing a liquid oxygen (LOx) and an ethanol injector: the good agreement between the model and the experimental results leads to the construction of the injectors operational maps describing the injector behavior even in the presence of viscous effects.
© The Authors, published by EDP Sciences, 2019
This is an Open Access article distributed under the terms of the Creative Commons Attribution License (http://creativecommons.org/licenses/by/4.0), which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited.