EQUILIBRIUM FLOW PARAMETERS FOR THE LOX-RP1 SYSTEM IN LARGE ROCKET NOZZLES,
Abstract
The problem of ascertaining the extent of attainment of thermodynamic equilibrium during combustion in large rocket engines is discussed with reference to the LOXRP-1 system. Calculations were made of concentration, pressure, and temperature gradients in both large booster and sustainer engines. Rapid changes were found to occur in these parameters in the first foot of the nozzle. Cooling rates, exceeding 10 to the 7th power degrees R per second indicate little possibility of achieving equilibrium conditions during the initial phases of the expansion process. Since theoretical absolute reaction rate calculations are not sufficiently accurate to clarify this situation, determination of the rate of establishment of equilibrium must await experimental verification. Such experiments are required to provide needed information: (a) regarding the extent of equilibrium in existing rocket engines, and (b) for altering contours so that reversible thermodynamic equilibrium can be more nearly favored in all sections of the nozzle. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- May 15, 1958
- Accession Number
- AD0607845
Entities
People
- E. L. Colichman
- J. G. Logan
Organizations
- TRW Inc.