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타이틀	RP-2 Thermal Stability and Heat Transfer Investigation for Hydrocarbon Boost Engines
저자	VanNoord, J. L.;; Stiegemeier, B. R.
Keyword	COMBUSTION CHAMBERS;; HEAT TRANSFER;; HIGH PRESSURE;; HYDROCARBONS;; LIQUID ROCKET PROPELLANTS;; REGENERATIVE COOLING;; ROCKET NOZZLES;; TEST CHAMBERS;; THERMAL DECOMPOSITION;; THERMAL STABILITY
URL	http://hdl.handle.net/2060/20110000532
보고서번호	NASA/TM-2010-216917
발행년도	2010
출처	NTRS (NASA Technical Report Server)
ABSTRACT	A series of electrically heated tube tests were performed at the NASA Glenn Research Center s Heated Tube Facility to investigate the use of RP-2 as a fuel for next generation regeneratively cooled hydrocarbon boost engines. The effect that test duration, operating condition and test piece material have on the overall thermal stability and materials compatibility characteristics of RP-2 were evaluated using copper and 304 stainless steel test sections. The copper tests were run at 1000 psia, heat flux up to 6.0 Btu/in.2-sec, and wall temperatures up to 1180 F. Preliminary results, using measured wall temperature as an indirect indicator of the carbon deposition process, show that in copper test pieces above approximately 850 F, RP-2 begins to undergo thermal decomposition resulting in local carbon deposits. Wall temperature traces show significant local temperature increases followed by near instantaneous drops which have been attributed to the carbon deposition/shedding process in previous investigations. Data reduction is currently underway for the stainless steel test sections and carbon deposition measurements will be performed in the future for all test sections used in this investigation. In conjunction with the existing thermal stability database, these findings give insight into the feasibility of cooling a long life, high performance, high-pressure liquid rocket combustor and nozzle with RP-2.