Accession Number:

ADA244255

Title:

Transpiration Cooled Throat for Hydrocarbon Rocket Engines

Descriptive Note:

Final rept.

Corporate Author:

AEROJET PROPULSION DIV SACRAMENTO CA

Personal Author(s):

Report Date:

1991-12-01

Pagination or Media Count:

252.0

Abstract:

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.

Subject Categories:

  • Liquid Propellant Rocket Engines
  • Liquid Rocket Propellants

Distribution Statement:

APPROVED FOR PUBLIC RELEASE