AN INVESTIGATION OF THE PERFORMANCE OF VARIOUS MIXTURES OF HYDROGEN AND METHANE.
AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OHIO SCHOOL OF ENGINEERING
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The primary purpose of this study was to evaluate the performance of various mixtures of hydrogen and methane as a fuel with oxygen as an oxidizer. A computer program was used to provide the theoretical results at a chamber pressure of 60 psia and mixture ratios from 1.5 to 5.0. The fraction of methane in the fuel was varied from 0 to 1.0. Experimental results were obtained by using a small reverse flow rocket engine and three separate propellant feed systems with a mixing chamber to combine the hydrogen and methane prior to the gases entering the fuel manifold of the rocket. A non-linear degradation of characteristic exhaust velocity was found as the fraction of methane in the fuel was increased. The degradation with all methane as the fuel was 77 of the pure hydrogen-oxygen performance. Experimentally, the combustion efficiency was found to decrease with an increasing percentage of methane in the fuel. Author
- Liquid Rocket Propellants