HIGH CHAMBER PRESSURE ROCKETRY PROGRAM. BOOK 1
Abstract
The objective of this program was to investigate, by both experimental testing and supporting analytical studies, the feasibility and degree of advantage of high chamber pressure rocket engines using nitrogen tetroxide/50% UDMH--50% N2H4 propellants. Both uncooled and cooled thrust chambers were test-fired at the 3000-psia pressure level; supporting studies included a study of the gas-side heat transfer coefficient, a propellants investigation which included some advanced propellant combinations, and system studies to determine the degree of advantage of high chamber pressure. Two injector concepts were developed using uncooled chambers, one of which attained a performance level of 97%*. Cooling systems investigated during cooled chamber testing included regenerative cooling with both oxidizer and fuel, film cooling with oxidizer, thermal barrier coatings, and vortex cooling. Based on the test results and supporting studies, it is concluded that operation of engines at high chamber pressure is feasible, and that the optimum chamber pressure is in the range of 2500 to 3500 psia. The best potential cooling system for future advanced high-pressure engines is regenerative cooling using N2O4 in combination with a thermal barrier coating and film cooling.
Document Details
- Document Type
- Technical Report
- Publication Date
- Dec 01, 1965
- Accession Number
- AD0368640
Entities
Organizations
- Aerojet Rocketdyne Holdings