Open AccessCooling of high pressure rocket thrust chambers with liquid oxygen
Author(s) -
H. G. Price
Publication year - 1980
Publication title -
24th joint propulsion conference
Language(s) - English
Resource type - Conference proceedings
DOI - 10.2514/6.1980-1260
Subject(s) - liquid oxygen , liquid propellant rocket , rocket (weapon) , aerospace engineering , thrust , oxygen , rocket engine , materials science , rocket propellant , nuclear engineering , environmental science , aeronautics , physics , engineering , propellant , quantum mechanics
An experimental program using hydrogen and oxygen as the propellants and supercritical liquid oxygen (LOX) a^ the Caotant was conducted at 4,14 and 8,174 MN/m • (b00 and 1200 psia) Chamber prk7sSUre. The ob,iective was to demonstrate and provide experimental data on the followingo (1) The effect of LOX leaking into the combustion region through small cracks in the chamber wall. (1) Verification of the supercritical oxygen heat transfer correlation developed from heated tube experiments. Four thrust chambers with throat diameters of 0.06b m (z.b in.) were tested. Thr^e of these were cyclically tested to 4.14 MM/m (b00 psia) chamber pressure until a crack developed. One had 13 additional hot cyc]PS arrumulated with no apparent metal burning or distress. The fourth chamber was operated at b.274 MM/m l (1[00 psia) pressure to obtain steady state heat transfer data. Wall temperature measurements confirmed the hoot transfer correlation.
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