Transpiration Cooled Throat for Hydrocarbon Rocket Engines
AEROJET PROPULSION DIV SACRAMENTO CA
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This programs objective was to characterize the use of hydrocarbon fuels as transpiration coolants for rocket nozzle throats. The hydrocarbon fuels investigated in this program were RP-1 and methane. To adequately characterize the above transpiration coolants, a program was planned which would 1 predict engine system performance and life enhancements due to transpiration cooling of the throat region using analytical models, anchored with available data 2 a versatile transpiration cooled subscale rocket thrust chamber was designed and fabricated 3 the subscale thrust chamber was tested over a limited range of conditions, e.g., coolant type, chamber pressure, transpiration cooled length, and coolant flowrate and 4 detailed data analyses were conducted to determine the relationship between the key performance and life enhancement variables. Analysis of the RP-1 transpiration cooled nozzle data indicates that subscale nozzle RP-1 transpiration flowrates can be reduced by 67 of the value predicted by previous models. Extrapolation of these results indicates that the RP-1 transpiration flowrates for the full scale baseline 750 Klbf engine are reduced by 35. Maximum Isp increase for the full scale RP-1 engine is revised from 3 to 10 seconds over a complete regeneratively cooled nozzle. Data obtained so far consists of only one high flowrate, low wall temperature test condition. Based on a single tet point, the data should be considered promising but not conclusive.
- Liquid Propellant Rocket Engines
- Liquid Rocket Propellants