Hydrocarbon Fuel Thermal Performance Modeling based on Systematic Measurement and Comprehensive Chromatographic Analysis
Technical Report,04 Jan 2016,31 Jul 2016
Air Force Research Laboratory (AFMC) AFRL/RQRC Edwards AFB United States
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In a typical hydrocarbon-fueled liquid rocket engine, enthalpy is removed from the combustion chamber by a regenerative cooling system comprising a series of passages through which fuel flows at high pressure and velocity, thereby maintaining the thrust chamber surface at acceptably low temperature. Ensuring reliable and predictable fuel thermal performance and material compatibility in cooling passages is crucial, particularly as engine operating conditions and lifecycle requirements extend beyond the domestic experience base. In addition to the extreme thermal-material environments accompanying advanced propulsion cooling systems and the multifaceted physicochemical processes of fuel degradation and surface fouling, clear understanding of fuel thermal behavior is inhibited by chemical complexity and compositional variability, which can occur as a result of fuel production method, refining conditions, treatment processes, and blending.
- Liquid Rocket Propellants
- Test Facilities, Equipment and Methods
- Physical Chemistry