Numerical analysis of bipropellant combustion in orbit maneuvering vehicle thrust chamberThe combustion and aerodynamic processes of liquid-liquid bipropellant; monomethylhydrazine and nitrogen tetroxide in the combustion chamber of a variable thrust engine (VTE) have been examined to assess the flow structure, combustion characteristics, and wall heat transfer under the simulated engine operations at two power levels. The Generalized Elliptic Multi-phase flow with Chemical reaction, Heat transfer and Interfacial Processes (GEM-CHIP) code and the Bipropellant Combustion (BICOMB) code, which is the GEMCHIP algorithm reformulated in the frame work of a body fitted coordinate system, have been used for the numerical study. Combustion flow structure with non-premixed type injection that simulates the impingement type injector is predicted and the results are compared with that of the premixed injector.
Document ID
19900039851
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Chiu, H. H. (Illinois Univ. Chicago, IL, United States)
Jiang, T. L. (Illinois, University Chicago, United States)
Krebsback, A. N. (Illinois Univ. Chicago, IL, United States)
Gross, K. W. (NASA Marshall Space Flight Center Huntsville, AL, United States)