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Experimental studies on piloted supersonic combustion using the petal nozzle
K. A. Damodaran
Published in American Institute of Aeronautics and Astronautics Inc.
1997
Volume: 13
   
Issue: 1
Pages: 142 - 149
Abstract
In recent times, high-speed, airbreathing propulsion research has been receiving considerable attention all over the world. This has come about primarily because of renewed interest in the development of reusable launch vehicles employing multimode propulsive systems. The scramjet, a critical subsystem of these composite engines, is still in the developmental stage. A crucial problem in this development is the realization of rapid mixing and heat release with minimum pressure losses inside the supersonic combustor. Recently, a new mixing technique for high-speed flows employing large-scale axial vortices was developed. This involved the use of a lobed supersonic primary nozzle referred to as the petal nozzle. The possibility of applying this novel mixing mechanism to piloted supersonic combustors was examined in this work. Results showed that rapid mixing took place between the hot primary (pilot) stream and the cold secondary airstream when the petal nozzle was used. Piloted secondary (supersonic) combustion of kerosene and acetylene was achieved with satisfactory efficiencies.
About the journal
JournalData powered by TypesetJournal of Propulsion and Power
PublisherData powered by TypesetAmerican Institute of Aeronautics and Astronautics Inc.
ISSN07484658
Impact Factor1.868
Open AccessNo
Citation Styleunsrt
Sherpa RoMEO Archiving PolicyGreen
Concepts (10)
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    Acetylene
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    Axial flow
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    Flow interactions
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    Kerosene
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    Nozzles
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    SUPERSONIC FLOW
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    Vortex flow
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    PETAL NOZZLE
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    SUPERSONIC COMBUSTOR
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    Combustors