Liquid oxygen cooling of high pressure LOX/hydrocarbon rocket thrust chambers

Technical Report · Fri Aug 01 04:00:00 EDT 1986

OSTI ID:6768514

Price, H G; Masters, P A

An experimental program using liquid oxygen (LOX) and RP-1 as the propellants and supercritical LOX as the coolant was conducted at 4.14, 8.27, and 13.79 MN/sq m (600, 1200, and 2000 psia) chamber pressure. The objectives of this program were to evaluate the cooling characteristics of LOX with the LOX/RP-1 propellants, the buildup of the soot on the hot-gas-side chamber wall, and the effect of an internal LOX leak on the structural integrity of the combustor. Five thrust chambers with throat diameters of 6.6 cm (2.5 in.) were tested successfully. The first three were tested at 4.14 MN/sq m (600 psia) chamber pressure over a mixture ratio range of 2.25 to 2.92. One of these three was tested for over 22 cyclic tests after the first through crack from the coolant channel to the combustion zone was observed with no apparent metal burning or distress. The fourth chamber was tested at 8.27 MN/sq m (1200 psia) chamber pressure over a mixture range of 1.93 to 2.98. The fourth and fifth chambers were tested at 13.79 MN/sq m (2000 psia) chamber pressure over a mixture ratio range of 1.79 to 2.68.

• Research Organization: National Aeronautics and Space Administration, Cleveland, OH (USA). Lewis Research Center
• OSTI ID: 6768514
• Report Number(s): N-87-14426; NASA-TM-88805; E-3149; NAS-1.15:88805
• Country of Publication: United States
• Language: English

Related Subjects

42 ENGINEERING
421000* -- Engineering-- Combustion Systems
COMBUSTION CHAMBERS
COOLING
DATA
ENERGY TRANSFER
ENGINES
EXPERIMENTAL DATA
HEAT TRANSFER
HIGH PRESSURE
INFORMATION
NUMERICAL DATA
PROPELLANTS
ROCKET ENGINES
SOOT