Accession Number : AD0853296

Title :   Development of Injector Chamber Compatibility Analysis for Task II.

Descriptive Note : Technical rept. Mar 68-Apr 69,

Corporate Author : ROCKETDYNE CANOGA PARK CA

Personal Author(s) : Hines, W. S. ; Combs, L. P. ; Ford, W. M.

Report Date : 01 JUN 1969

Pagination or Media Count : 226

Abstract : A system of computer programs is described which calculates the effect of injector configuration on ablative wall response. The distribution of propellant spray near the injector is calculated from a correlation based upon cold-flow data, and this distribution is used as input to a droplet burning modle which calculates the three-dimensional combustion gas flow field. A multiple stream tube analysis is used in the nozzle region. Local boundary layers are calculated based upon the gas temperature, composition, and velocity field adjacent to the chamber walls. Transient conduction programs calculate the ablation and erosion of the chamber walls. An experimental program consisting of cold-flow tests and model motor firings with NTO/mixed hydrazines fuel was conducted to support the analytical program. (Author)

Descriptors :   (*LIQUID PROPELLANT ROCKET ENGINES, COMBUSTION CHAMBERS), (*COMBUSTION CHAMBERS, INJECTORS), ORIFICES, LIQUID ROCKET PROPELLANTS, COMBUSTION CHAMBER GASES, THREE DIMENSIONAL FLOW, EXHAUST NOZZLES, NOZZLE GAS FLOW, ENTHALPY, ABLATION, EROSIVE BURNING, MATHEMATICAL MODELS, FLOW CHARTING, COMPUTER PROGRAMMING.

Subject Categories : Combustion and Ignition
      Liquid Propellant Rocket Engines

Distribution Statement : APPROVED FOR PUBLIC RELEASE