Combustion performance of bipropellant liquid rocket engine combustors with fuel-impingement cooling
Journal Article
·
· Journal of Propulsion and Power
- Natl Cheng Kung Univ., Tainan, Taiwan (China)
In order to obtain an accurate combustion analyses which are important in the thruster design of modern advanced liquid rocket engine, flow analysis should be conducted from the injector phase down to the propulsive nozzle throat. Thus, in the present study, flow analysis for the axisymmetric thrust chamber of an OMV(exp 3) installed with a pintle-type ring-shaped injector and a conical convergent nozzle is conducted. Liquid monomethyl hydrazine (MMH) and nitrogen tetroxide (NTO) storable bipropellants are used as fuel and oxidizer sources. An optimum injected fuel and oxidizer droplet-size combination is proposed. Finally, the results obtained are presented. 4 refs.
- Sponsoring Organization:
- USDOE
- OSTI ID:
- 117645
- Journal Information:
- Journal of Propulsion and Power, Journal Name: Journal of Propulsion and Power Journal Issue: 3 Vol. 11; ISSN 0748-4658; ISSN JPPOEL
- Country of Publication:
- United States
- Language:
- English
Similar Records
Optimum performance of MHD-augumented chemical rocket thrusters for space propulsion applications
Hydrogen peroxide-based propulsion and power systems.
Molecular beam sampling from a rocket-motor combustion chamber
Conference
·
Sat Dec 30 23:00:00 EST 1995
·
OSTI ID:254666
Hydrogen peroxide-based propulsion and power systems.
Technical Report
·
Wed Mar 31 23:00:00 EST 2004
·
OSTI ID:903157
Molecular beam sampling from a rocket-motor combustion chamber
Conference
·
Mon Dec 31 23:00:00 EST 1973
·
OSTI ID:4138757