Comparative Analysis of the Detonation Combustion of Kerosene and Gasoline Vapors in a Laval Nozzle

Abstract

The possibility of stabilizing the detonation combustion of kerosene and gasoline vapors in a supersonic air flow entering an axisymmetric convergent-divergent nozzle with a central body under atmospheric conditions at an altitude of 16 km is studied numerically. The central body provides direct initiation of detonation due to the thermal and kinetic energy of the incident flow. The mathematical model is based on twodimensional unsteady Euler equations for an axisymmetric flow of a multicomponent reacting gas and reduced kinetic models of combustion of flammable mixtures. The calculations use a modification of the numerical scheme of S.K. Godunov of the second order of accuracy in spatial variables. The central body of the cylinder-cone (CC) and cone-cylinder-cone (CCC) types is considered. The possibility of stabilizing the detonation combustion of kerosene at the oncoming flow of Mach numbers of M = 7 and 9 with thrust generation is shown. In the case of gasoline, only a small part of the mixture burns in the detonation mode behind the detached shock wave in front of the end wall of the central body. The thrust obtained in gasoline vapors does not compensate the aerodynamic resistance of the nozzle and the central body.