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Effect of fuel temperature on supersonic combustion

M. Wendt, R. J. Stalker, Peter A. Jacobs

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Abstract

A. combined exnerimental and comDutational study of the effect of fuel stagnation temperature on mixing in a supersonic hydrogen-air flame is described. The combustor consisted of a constant-area rectangular duct with a centrally located fuel injector strut. A high enthalpy stream of air was supplied by a free-piston shock tunnel and heated hydrogen fuel was injected into the free stream as a co-flowing planar jet. The free stream total enthalpies were 5. 6, 6.5 and 9 MJ/kg and fuel stagnation temperatures were 300 K, 450 K and 700 K. Raising the fuel temperature increased the fuel velocity to be near that of the air stream and resulted in a decrease in the mixing rate. This trend agreed with previous, low enthalpy studies. The flow downstream of the injector was simulated using a parabolised Navier Stokes code and the results were used to identify the effect of fuel temperature on supersonic combustion.

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What this paper is about

A. combined exnerimental and comDutational study of the effect of fuel stagnation temperature on mixing in a supersonic hydrogen-air flame is described. The combustor consisted of a constant-area rectangular duct with a centrally located fuel injector strut. A high enthalpy stream of air was supplied by a free-piston shock tunnel and heated hydrogen fuel was injected into the free stream as a co-flowing planar jet. The free stream total enthalpies were 5. 6, 6.5 and 9 MJ/kg and fuel stagnation temperatures were 300 K, 450 K and 700 K. Raising the fuel temperature increased the fuel velocity to be near that of the air stream and resulted in a decrease in the mixing rate. This trend agreed with previous, low enthalpy studies. The flow downstream of the injector was simulated using a parabolised Navier Stokes code and the results were used to identify the effect of fuel temperature on supersonic combustion.

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Available abstract

A. combined exnerimental and comDutational study of the effect of fuel stagnation temperature on mixing in a supersonic hydrogen-air flame is described. The combustor consisted of a constant-area rectangular duct with a centrally located fuel injector strut. A high enthalpy stream of air was supplied by a free-piston shock tunnel and heated hydrogen fuel was injected into the free stream as a co-flowing planar jet. The free stream total enthalpies were 5. 6, 6.5 and 9 MJ/kg and fuel stagnation temperatures were 300 K, 450 K and 700 K. Raising the fuel temperature increased the fuel velocity to be near that of the air stream and resulted in a decrease in the mixing rate. This trend agreed with previous, low enthalpy studies. The flow downstream of the injector was simulated using a parabolised Navier Stokes code and the results were used to identify the effect of fuel temperature on supersonic combustion.

Key concepts: Combustion, Supersonic speed, Environmental science, Materials science, Automotive engineering, Aerospace engineering, Engineering, Chemistry

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