Experimental investigation of H2 combustion and supersonic cooling in an annular channel
- 30 Downloads
Results are presented for an experimental investigation of H2 combustion and cooling in a channel which simulates the intake and combustion chamber of a supersonic ram jet. Stable operation conditions were obtained for operating the intake and combustion chamber with various fuel distributions through the feed zones. The cooling rate and the combustion efficiency were determined at the chamber wall at varying flows in the channel.
KeywordsCombustion Dynamical System Mechanical Engineer Cool Rate Experimental Investigation
Unable to display preview. Download preview PDF.
- 1.Hypersonic Research Engine Project. Phase 2: Aerothermodynamic Intergation Model Development (1968).Google Scholar
- 2.F. S. Billig, G. L. Dugger, and P. J. Waltrup, “Inlet-combustor interface problems in scramjet engines,” First International Symposium on Air Breathing Engines, June 19–23, 1972, Marseilles, France.Google Scholar
- 3.P. J. Waltrup, G. Y. Anderson, and F. D. Stull, “Supersonic combustion ramjet engine development in the United States,” Third International Symposium on Air Breathing Engines, Munich, Germany (1976).Google Scholar
- 4.V. K. Baev, V. V. Shumskii, and M. I. Yaroslavtsev, “Investigation of the pressure distribution and heat transfer in a gas dynamic model with combustion and a high-enthalpy air flow,” Zh. Prikl. Mekh. Tekh. Fiz., No. 5, 56–65 (1985).Google Scholar
- 5.V. K. Baev, V. V. Shumskii, and M. I. Yaroslavtsev, “Some aspects of techniques of investigating gas dynamic models with heat and mass transfer in a pulsed aerodynamic tube,” Fiz. Goreniya Vzryva,23, No. 5, 45–54 (1987).Google Scholar
- 6.V. S. Avduevskii, “Method of calculating a distributed turbulent boundary layer in compressed gas,” Izv. Akad. Nauk SSSR, Mekh. Zhidk. Gaza, No. 4, 3–12 (1962).Google Scholar