Numerical analysis of bipropellant combustion in orbit maneuvering vehicle thrust chamber

H. H. Chiu, Tsung-Leo Jiang, A. N. Krebsback, K. W. Gross

Research output: Contribution to conferencePaper

1 Citation (Scopus)

Abstract

The 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.

Original languageEnglish
Publication statusPublished - 1990 Jan 1
Event28th Aerospace Sciences Meeting, 1990 - Reno, United States
Duration: 1990 Jan 81990 Jan 11

Other

Other28th Aerospace Sciences Meeting, 1990
CountryUnited States
CityReno
Period90-01-0890-01-11

Fingerprint

Numerical analysis
Orbits
Flow structure
Engines
Air cushion vehicles
Multiphase flow
Liquids
Combustion chambers
Chemical reactions
Aerodynamics
Heat transfer
Nitrogen

All Science Journal Classification (ASJC) codes

  • Aerospace Engineering

Cite this

Chiu, H. H., Jiang, T-L., Krebsback, A. N., & Gross, K. W. (1990). Numerical analysis of bipropellant combustion in orbit maneuvering vehicle thrust chamber. Paper presented at 28th Aerospace Sciences Meeting, 1990, Reno, United States.
Chiu, H. H. ; Jiang, Tsung-Leo ; Krebsback, A. N. ; Gross, K. W. / Numerical analysis of bipropellant combustion in orbit maneuvering vehicle thrust chamber. Paper presented at 28th Aerospace Sciences Meeting, 1990, Reno, United States.
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Chiu, HH, Jiang, T-L, Krebsback, AN & Gross, KW 1990, 'Numerical analysis of bipropellant combustion in orbit maneuvering vehicle thrust chamber' Paper presented at 28th Aerospace Sciences Meeting, 1990, Reno, United States, 90-01-08 - 90-01-11, .

Numerical analysis of bipropellant combustion in orbit maneuvering vehicle thrust chamber. / Chiu, H. H.; Jiang, Tsung-Leo; Krebsback, A. N.; Gross, K. W.

1990. Paper presented at 28th Aerospace Sciences Meeting, 1990, Reno, United States.

Research output: Contribution to conferencePaper

TY - CONF

T1 - Numerical analysis of bipropellant combustion in orbit maneuvering vehicle thrust chamber

AU - Chiu, H. H.

AU - Jiang, Tsung-Leo

AU - Krebsback, A. N.

AU - Gross, K. W.

PY - 1990/1/1

Y1 - 1990/1/1

N2 - The 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.

AB - The 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.

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M3 - Paper

ER -

Chiu HH, Jiang T-L, Krebsback AN, Gross KW. Numerical analysis of bipropellant combustion in orbit maneuvering vehicle thrust chamber. 1990. Paper presented at 28th Aerospace Sciences Meeting, 1990, Reno, United States.