MODELING OF KEROSENE COMBUSTION IN A SUPERSONIC FLOW UNDER THE ACTION OF A THROTTLING JET
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MODELING OF KEROSENE COMBUSTION IN A SUPERSONIC FLOW UNDER THE ACTION OF A THROTTLING JET V. P. Zamuraev and A. P. Kalinina∗
UDC 533.6.011
Abstract: Structural changes in a supersonic flow in a variable-section channels with axial injection of kerosene induced by the action of a jet generating a throttling effect are numerically simulated. Reynolds-averaged Navier–Stokes equations closed by the k–ε turbulence model are solved. Kerosene combustion is modeled by equations of simplified chemical kinetics. The evolution of the processes in the channel is analyzed numerically and analytically for different types of the fuel (hydrogen, ethylene, and kerosene), and comparisons with experimental data are performed. It is found that high-intensity gas-dynamic pulses have to be used to form a transonic region in the case where kerosene is used as a fuel. Keywords: kerosene combustion, axial injector, supersonic flow, throttling jet, transonic regime. DOI: 10.1134/S0021894420050107
INTRODUCTION The problem of combustion organization in a supersonic flow is associated with the development of flying vehicles intended to fly at high flight Mach numbers. The number of needed experiments can be reduced by using numerical simulations, which can also provide characteristics of the process that cannot be obtained experimentally. In this case, however, the models of turbulence and chemical kinetics are chosen with some arbitrariness. In choosing these models, one has to define the values of the physical and chemical parameters. The present paper describes the numerical simulations of the first stage of the two-stage process of initiation of the combustion chamber of a ramjet [1–3], in particular, investigations of the influence of physical and chemical parameters on the development of the processes in the combustion chamber with the use of one system of equations for different types of gaseous fuels. The first stage of this two-stage process implies preliminary deceleration of the supersonic flow in the constant-section channel to transonic velocities. In this section, the gaseous fuel (hydrogen, ethylene, or kerosene) is injected in the a sufficient amount for flow deceleration to the transonic velocity in the case of complete combustion of the fuel. A throttling jet of compressed air is injected into the channel to initiate ignition and combustion. The pressure in the gas generator of this jet is several times higher than the pressure in the main flow in the channel. As a result, a shock wave is formed ahead of the jet, which initiates the processes of fuel ignition and combustion. The initiation method proposed in [1–3] differs from other methods [4–10] by the fact that it can simultaneously solve the problems of mixing, ignition, and combustion with a small total pressure loss.
Khristianovich Institute of Theoretical and Applied Mechanics, Siberian Branch, Russian Academy of Sciences, Novosibirsk, 630090 Russia; [email protected]; ∗ [email protected]. Translated from Prikladnaya Mekhanika i Tekhnicheskaya Fizika, Vol. 61, No. 5, pp. 95–100, S
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