Abstract
Based on studies of the flow structure in a short cylindrical vortex chamber, the dependence of the flow rate coefficient on its geometric parameters is proposed. It is shown that the liquid flow form in the chamber’s axial vortex the pressure on which surface is corresponds to the pressure of the outflow cavity. These results are used to measure pressure in high-temperature cavities, using a sleeve with a diameter equal to or slightly larger than the diameter of the axial vortex. The sleeve is installed in the vortex chamber, and connects the pressure on its surface to the pressure sensor. The possibility of using a vortex chamber as a damper of pressure fluctuations has been substantiated. The design of the vortex damper and its tests results are presented; these show the possibility of increasing the stabilization time of the outlet pressure more than three-fold. Variants of regulating devices with a vortex chamber, functioning without changing the flow cross-sections, are proposed and the results of their tests are presented. This is achieved either by introducing an obstacle into the chamber cavity or by displacing the axis of the outlet nozzle position.
-
Author contributions: The author has accepted responsibility for the entire content of this submitted manuscript and approved submission.
-
Research funding: None declared.
-
Conflict of interest statement: The author declares no conflicts of interest regarding this article.
References
1. Anderson, WE, Yang, V. Liquid rocket engine combustion instability. Washington, US: American Institute of Aeronautics and Astronautics; 1995.Search in Google Scholar
2. Pérez-Roca, S, Marzat, J, Piet-Lahanier, H, Langlois, N, Farago, F, Galeotta, M, et al.. A survey of automatic control methods for liquid-propellant rocket engines. Prog Aero Sci 2019;107:63–84. https://doi.org/10.1016/j.paerosci.2019.03.002.Search in Google Scholar
3. Sakaki, K, Funahashi, T, Nakaya, S, Tsue, M, Kanai, R, Suzuki, K, et al.. Longitudinal combustion instability of a pintle injector for a liquid rocket engine combustor. Combust Flame 2018;194:115–27. https://doi.org/10.1016/j.combustflame.2018.04.017.Search in Google Scholar
4. Mersinligil, M, Brouckaert, JFO, Desset, J. First unsteady pressure measurements with a fast response cooled total pressure probe in high temperature gas turbine environments. In: Turbo expo: power for land, sea, and air. Glasgow, UK: International Gas Turbine Institute; 2010, 43987:385–400 pp.Search in Google Scholar
5. Bengtsson, KU, Benz, P, Schären, R, Frouzakis, CE. NyOx formation in lean premixed combustion of methane in a high-pressure jet-stirred reactor. In: Symposium (international) on combustion. Colorado, US: The University of Colorado at Boulder; 1998, 27:1393–9 pp.Search in Google Scholar
6. Bertsch, R, Gunther, D, Knapp, H, Plapp, G. Fuel supply line. U.S. Patent No. 4,660,524, 1987.Search in Google Scholar
7. Talaski, EJ. Fuel pump tubular pulse damper. U.S. Patent No. 5,516,266, 1996.Search in Google Scholar
8. Conley, JA, McNeely, MD. Pulsation damping assembly and method. U.S. Patent No. 6,478,052, 2002.Search in Google Scholar
9. Fox, LS. Hydrogen flow rate control: the use of fixed and adjustable sonic chokes for simple, reliable, inexpensive H2 flow control. In: The 14th world hydrogen energy conference. Canada; 2002.Search in Google Scholar
10. Van Toor, MW, Lammerink, TS, Gardeniers, JG, Elwenspoek, M, Monsma, D. A novel micromechanical flow controller. J Micromech Microeng 1997;7:165. https://doi.org/10.1088/0960-1317/7/3/023.Search in Google Scholar
11. Isselin, JC, Alloncle, AP, Autric, M. On laser induced single bubble near a solid boundary: contribution to the understanding of erosion phenomena. J Appl Phys 1998;84:5766–71. https://doi.org/10.1063/1.368841.Search in Google Scholar
12. Gupta, A, Lily, D, Cyred, N. Swirling flows. Tunbridge Wells, England: M.: World; 1987.Search in Google Scholar
13. Uss, AY, Chernyshev, AV. The development of the vortex gas pressure regulator. Procedia Eng 2016;152:380–8. https://doi.org/10.1016/j.proeng.2016.07.718.Search in Google Scholar
14. Wei, XG, Li, J, He, GQ. Swirl characteristics of vortex valve variable-thrust solid rocket motor. J Appl Fluid Mech 2018;11:205–15. https://doi.org/10.29252/jafm.11.01.27658.Search in Google Scholar
15. Levitsky, MP. Cavitation characteristics of the orifice with swirled outflow. In: International symposium on multi-phase flow and transport phenomena. Turkey; 2000.Search in Google Scholar
16. Wormley, DN. An analytical model for the incompressible flow in short vortex chambers. J Basic Eng; 196991:264–72.Search in Google Scholar
17. Koval, VP, Mikhailov, SP. Velocity and pressure distribution at liquid flow in a vortex chamber. Thermoenergetics 1972;2:172–7.Search in Google Scholar
18. Khavkin, YI. Theory and practice of swirl atomizers. Bosa Roca, US: CRC Press; 2003.Search in Google Scholar
19. Dityakin, YF, Klyachko, LA, Novikov, BV, Yagodkin, VI. Atomization of liquids. Moscow: Mashinostroenie; 1977. p. 207.Search in Google Scholar
20. Datta, A, Som, SK. Numerical prediction of air core diameter, coefficient of discharge and spray cone angle of a swirl spray pressure nozzle. Int J Heat Fluid Flow 2000;21:412–9. https://doi.org/10.1016/s0142-727x(00)00003-5.Search in Google Scholar
21. Halder, MR, Dash, SK, Som, SK. Initiation of air core in a simplex nozzle and the effects of operating and geometrical parameters on its shape and size. Exp Therm Fluid Sci 2002;26:871–8. https://doi.org/10.1016/s0894-1777(02)00153-x.Search in Google Scholar
22. Kotowski, A, Wojtowicz, P. Analysis of hydraulic parameters of cylindrical vortex regulators. Environ Protect Eng 2008;34:43.Search in Google Scholar
23. Kotowski, A, Wójtowicz, P. Analysis of hydraulic parameters of conical vortex regulators. Pol J Environ Stud 2010;19:749–56.Search in Google Scholar
24. Borisenko, AI. Gas dynamics of engines. Moscow: Oborongiz; 1962.Search in Google Scholar
© 2021 Walter de Gruyter GmbH, Berlin/Boston
