LOX cooled thrust chamber technology developments

Abstract

An experimental LOX heat-transfer study and a LOX-cooled thrust-chamber demonstration program are summarized. Heat transfer to supercritical oxygen was investigated at 17 to 34.5 MPa (2460 to 5000 psia), and heat fluxes up to 90 MW/sq m (55 Btu/sq in.-sec). Experimental data obtained previously were correlated along with these recent data, and a design equation was derived which correlates 95% of the data within + or - 30%. Liquid-oxygen-cooled thrust chambers have been designed using this correlation and are currently being fabricated. A test program is planned for evaluating the LOX-cooled design concept using NASA test facilities. The purpose of these tests is to verify the LOX cooling correlation in a high-pressure liquid rocket engine and to determine the effects of a LOX coolant leak.