Flame air heater for wide-range scramjet combustor research

Аuthors

Avrashkov V. N.^*, Metelkina E. S.^*, Meshcheriakov D. V.^*

Moscow Aviation Institute (National Research University), 4, Volokolamskoe shosse, Moscow, А-80, GSP-3, 125993, Russia

*e-mail: aerospace@mai.ru

Abstract

A design of three-stage heater is proposed and realized to generate high-enthalpy model flow at a ground-based test-bench for combustion chambers of dual-mode scramjet research in conditions of connected-pipe test facility. A number of experiments are carried out to measure stagnation temperature fields at outlet from supersonic nozzles mounted on the heater. Test results obtained in the experiments demonstrate that the three-stage heater design is able to simulate effectively flight conditions for Mach number range M=2 ÷ 7,5 and for altitude values range H=0 ÷ 38 km. A numerical model of the heater is described basing on thermodynamic calculations. The model is intended to identify characteristics of model flow generated with the heater as well as to diagnose operating conditions of the heater.

Keywords:

flame heater; test-bench; connected air duct; supersonic flow; combustion chamber; scramjet; Mach number, mathematical model