Experimental study of the ignition of liquid hydrocarbon fuels and stabilization of their combustion by an arc discharge
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AND VACUUM DISCHARGES
Experimental Study of the Ignition of Liquid Hydrocarbon Fuels and Stabilization of Their Combustion by an Arc Discharge V. A. Bityurina, V. Yu. Velikodnyia, B. N. Tolkunova, A. A. Bykovb, A. V. Dyrenkovb, and V. V. Popovc a
Joint Institute for High Temperatures (IVTAN), Russian Academy of Sciences, Izhorskaya ul. 13/19, Moscow, 127412 Russia b Moscow Institute of Physics and Technology, Institutskii per. 9, Dolgoprudnyi, Moscow oblast, 141700 Russia c Institute of Applied Mechanics, Russian Academy of Sciences, Leninskii pr. 32a, Moscow, 117312 Russia email: [email protected], Aleks[email protected] Received December 6, 2010
Abstract—The ignition of liquid hydrocarbon fuels and stabilization of their combustion by an arc discharge in a supersonic air flow are investigated experimentally. The discharge parameters and flame characteristics (ignition time lag) are determined. It is shown that the average energy deposited in the flow by the igniter is five orders of magnitude less than the kinetic energy of the main gas flow. DOI: 10.1134/S1063780X12100030
INTRODUCTION The investigation of the ignition and maintenance of combustion of liquid hydrocarbon fuels in air by various types of electric discharges is an actual prob lem for aviation, power engineering, and other branches of the national economy [1–5]. Combustion in multiphase media which use high molecular hydrocarbons (kerosene, diesel oil, oil, fuel oil) as fuel is difficult by itself for theoretical calcula tion and study, particularly, in a time of combustion initiation; therefore, experimental investigation meth ods have come forward for solving the given problem. One of the unresolved problems is the ignition and maintenance of stable combustion of kerosene during the flight of aircrafts with a ramjet at high heights at Mach numbers of 3 ≤ M ≤ 5 in the approach flow [3, 5]. The problem is that the efficiency of turbojet engines falls abruptly at M ≥ 3 in the approach flow, and the air temperature within a ramjet intake at 3 ≤ M ≤ 5 in the approach flow is insufficient for the stable ignition and maintenance of stable combustion of avi ation kerosene. At present, for launching and testing experimental models of aircrafts, as a rule, a carrier aircraft is used, and further, the model is preacceler ated by its solidpropellant rocket engine to Mach numbers where the ignition and combustion of kero sene become stable. It is clear that such a scheme is improper for actual apparatuses starting from the ground; therefore, various methods of ignition and combustion stabilization in the supersonic flow are considered. These are hydrogen and silane additions [6], fuel modification with the use of barbotage and shockwave treatment (socalled activated porous
fuel), and doublecircuit systems for fuel feeding into a combustion chamber [1, 3, 5]. One of prospective directions is the use of various types of electric dis charges, including an arc one, for ignition and flame maintenance in the supersonic flow. Investigations are concen
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