INFLUENCE OF ACCELERATION ON COMBUSTION IN A ROCKET ENGINE.
Abstract
The influence of acceleration was analyzed under the following assumptions: The velocity distribution of the quasi-one-dimensional steady state flow through the nozzle is linear in the axial variable. Combustion occurs at a fixed point in the nozzle and at a constant temperature. Burning rate for a solid propellant is proportional to a power n of the chamber pressure. For a liquid propellant with injection rate unaffected by the acceleration, the ratio of burning rate to injection rate is equal to the power of n of the ratio of the instantaneous pressure and the pressure at an earlier time determined by the time lag in the combustion process. For the liquid propellant with time lag, instability occurs for some values of time lag and of the burning rate parameter n. From the linearized solutions, a stability diagram was drawn in the plane of the time lag and burning rate parameter n. Increasing either time lag or the combustion rate exponent from neutrally stable values produces instability. The effect of increasing the magnitude of acceleration appears to shift the neutral curve to lower values of time lag and the burning rate exponent. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Jun 01, 1966
- Accession Number
- AD0638993
Entities
People
- F. Edward Ehlers
Organizations
- Boeing