Investigation of the transient fuel preburner manifold and combustor. Final report

Technical Report · Thu Jun 01 04:00:00 EDT 1989

OSTI ID:5304007

Wang, Tensee; Chen, Yensen; Farmer, R C

A computational fluid dynamics (CFD) model with finite rate reactions, FDNS, was developed to study the start transient of the Space Shuttle Main Engine (SSME) fuel preburner (FPB). FDNS is a time accurate, pressure based CFD code. An upwind scheme was employed for spatial discretization. The upwind scheme was based on second and fourth order central differencing with adaptive artificial dissipation. A state of the art two-equation k-epsilon (T) turbulence model was employed for the turbulence calculation. A Pade' Rational Solution (PARASOL) chemistry algorithm was coupled with the point implicit procedure. FDNS was benchmarked with three well documented experiments: a confined swirling coaxial jet, a non-reactive ramjet dump combustor, and a reactive ramjet dump combustor. Excellent comparisons were obtained for the benchmark cases. The code was then used to study the start transient of an axisymmetric SSME fuel preburner. Predicted transient operation of the preburner agrees well with experiment. Furthermore, it was also found that an appreciable amount of unburned oxygen entered the turbine stages.

• Research Organization: SECA, Inc., Huntsville, AL (USA); SECA, Inc., Huntsville, AL (USA)
• OSTI ID: 5304007
• Report Number(s): N-89-26900; NASA-CR--183715; NAS--1.26:183715; SECA--89-10
• Country of Publication: United States
• Language: English

Related Subjects

42 ENGINEERING
421000* -- Engineering-- Combustion Systems
ALGORITHMS
COMBUSTION CHAMBERS
DOCUMENT TYPES
FLOW MODELS
FLUID FLOW
MATHEMATICAL LOGIC
MATHEMATICAL MODELS
PROGRESS REPORT