Numerical grid generation and flow simulation in SSME thrust chamber

Book · Thu Jan 01 00:00:00 EST 1987

OSTI ID:7012212

Gross, K W; Daley, P L; Przekwas, A J

The development of liquid and solid rocket engines for future space projects demands a detailed optimization process for highly efficient performance and cost reasons. Also, testing of full size engines may not be feasible when the large size requires test facilities which are cost prohibitive or if vacuum operation cannot be acquired. For such situations only scaling from small test scale measurements or accurate analytical predictions will provide the performance prior to actually flying the mission. A rigorous approach for simulating the combustion processes in liquid rocket engines by employing a direct solution of Navier-Stokes equations within the entire volume of the thrust chambers is presented. This method is illustrated in the solution of reactive flow in the Space Shuttle Main Engine (SSME) thrust chamber. The objective is to review recent improvements in the mathematical model and to present the grid generation methodology suitable for rocket thrust chamber geometries.

• Research Organization: National Aeronautics and Space Administration, Huntsville, AL (USA). George C. Marshall Space Flight Center
• OSTI ID: 7012212
• Country of Publication: United States
• Language: English

Related Subjects

37 INORGANIC
ORGANIC
PHYSICAL AND ANALYTICAL CHEMISTRY
42 ENGINEERING
COMBUSTION CHAMBERS
COMBUSTION KINETICS
MATHEMATICAL MODELS
ROCKET ENGINES
ALGORITHMS
COMPUTERIZED SIMULATION
THEORETICAL DATA
TRANSONIC FLOW
CHEMICAL REACTION KINETICS
DATA
ENGINES
FLUID FLOW
INFORMATION
KINETICS
MATHEMATICAL LOGIC
NUMERICAL DATA
REACTION KINETICS
SIMULATION
400800* - Combustion
Pyrolysis
& High-Temperature Chemistry
421000 - Engineering- Combustion Systems