A Film Cooling Model for a RP-1/GOX Staged Combustion Liquid Rocket Engine (Preprint)
Abstract
An experimental study of supercritical RP-1 film cooling was conducted in a RP-1/GOX rocket combustor. A heat sink test section, heavily instrumented with dual Type E coaxial thermocouples, was used for measurement of wall temperature and derived gas-side wall heat flux. Varying amounts of fuel, ranging from about 40% to 70% of the total fuel flowrate, were injected as a film coolant downstream of a coaxial injector element. An existing film cooling model was modified and applied to these experimental results. The resultant model predicted combustion chamber adiabatic wall temperature profiles for input propellant flow conditions and chamber geometry. The predicted wall temperatures were compared with the experimental measurements to assess the model's performance. The film cooling model wall temperature predictions had errors ranging from near 0 to approx. 33% compared to the experimental results for four out of five analyzed tests.
Document Details
- Document Type
- Technical Report
- Publication Date
- Nov 07, 2007
- Accession Number
- ADA483024
Entities
People
- Daniel A. Greisen
- Philip A. Haberlen
- William E Anderson