Fuel stagnation temperature effects on mixing with supersonic combustion flows

Wendt, MN, Stalker, RJ and Jacobs, PA (1997) Fuel stagnation temperature effects on mixing with supersonic combustion flows. Journal of Propulsion And Power, 13 2: 274-280. doi:10.2514/2.5159


Author Wendt, MN
Stalker, RJ
Jacobs, PA
Title Fuel stagnation temperature effects on mixing with supersonic combustion flows
Journal name Journal of Propulsion And Power   Check publisher's open access policy
ISSN 0748-4658
Publication date 1997-01-01
Sub-type Article (original research)
DOI 10.2514/2.5159
Volume 13
Issue 2
Start page 274
End page 280
Total pages 7
Language eng
Abstract An experimental 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-injection strut that spanned the width. A high-enthalpy stream of air was supplied by a free-piston shock tunnel, and heated hydrogen fuel, supplied by a gun-tunnel, was injected into the freestream as a coflowing planar jet. The freestream total enthalpies were 5.6, 6.5, and 9 MJ/kg, and fuel stagnation temperatures were 300, 450, and 700 K, Raising the fuel stagnation temperature increased the fuel velocity to be near that of the airstream and resulted in a decrease in the mixing rate, Even as the fuel and air velocities became equal, significant mixing still occurred because of a large difference in density, Increasing the freestream enthalpy reduced the difference between the initial air temperature and the adiabatic flame temperature, which in turn reduced the heat addition, and subsequently, the amount of pressure rise in the duct.
Keyword Engineering, Aerospace
Q-Index Code C1
Q-Index Status Provisional Code
Institutional Status Unknown

Document type: Journal Article
Sub-type: Article (original research)
Collection: School of Mechanical & Mining Engineering Publications
 
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Created: Tue, 14 Aug 2007, 02:42:10 EST