Cooling of High-Pressure Rocket Thrust Chambers with Liquid Oxygen | Zendy

H. G. Price | Zendy

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Cooling of High-Pressure Rocket Thrust Chambers with Liquid Oxygen

Author(s) -

H. G. Price

Publication year - 1981

Publication title -

journal of spacecraft and rockets

Language(s) - English

Resource type - Journals

SCImago Journal Rank - 0.758

H-Index - 79

eISSN - 1533-6794

pISSN - 0022-4650

DOI - 10.2514/3.57826

Subject(s) - aerospace engineering , liquid oxygen , spacecraft , rocket (weapon) , missile , liquid propellant rocket , space launch , thrust , space (punctuation) , space shuttle , rocket engine , propellant , mechanical engineering , space environment , spacecraft design , aeronautics , engineering , space research , systems engineering , computer science , physics , oxygen , launch vehicle , quantum mechanics , operating system , geophysics

An experimental program using hydrogen and oxygen as the propellants and supercritical liquid oxygen (LOX) as the coolant was conducted at 4.14 and 8.274 MN/square meters (600 and 1200 psia) chamber pressure. Data on the following are presented: the effect of LOX leaking into the combustion region through small cracks in the chamber wall; and verification of the supercritical oxygen heat transfer correlation developed from heated tube experiments; A total of four thrust chambers with throat diameters of 0.066 m were tested. Of these, three were cyclically tested to 4.14 MN/square meters (600 psia) chamber pressure until a crack developed. One had 23 additional hot cycles accumulated with no apparent metal burning or distress. The fourth chamber was operated at 8.274 MN/square meters (1200 psia) pressure to obtain steady state heat transfer data. Wall temperature measurements confirmed the heat transfer correlation.

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