Testing the liquid fuel injector in cold flow using a supersonic wind tunnel

This paper aims to deal the new idea of liquid fuel (kerosene) aeroramp injector/plasma igniter who was tested in cold flow using a supersonic wind tunnel at Mach 2.4. The liquid fuel injector is flush wall mounted and consists of a 2 holes aeroramp array of impinging jets that are oriented in a man...

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Bibliographic Details
Published inAnnals of DAAAM & proceedings p. 941
Main Authors Stan, Liviu-Constantin, Mitu, Daniela-Elena
Format Journal Article
LanguageEnglish
Published DAAAM International Vienna 01.01.2010
Subjects
Dynamic testing
Equipment and supplies
Methods
Ultrasonics
Wind tunnels
Romania
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Summary:This paper aims to deal the new idea of liquid fuel (kerosene) aeroramp injector/plasma igniter who was tested in cold flow using a supersonic wind tunnel at Mach 2.4. The liquid fuel injector is flush wall mounted and consists of a 2 holes aeroramp array of impinging jets that are oriented in a manner to improve mixing and atomization of the liquid jets. Scramjet combustion is a difficult and daunting task to tackle. Among other problems, there is the difficulty in mixing and ignition of fuel, especially hydrocarbons in a supersonic flow. A substantial amount of research has been performed in the field of gas injection in supersonic flows and included these techniques: transverse injection, slots, ramps and jet swirl. Key words: kerosene, fuel injector, supersonic tunnel
ISSN:1726-9679
1726-9679