ISSN Online: 2688-7231
ISBN Online: 978-1-56700-478-6
Proceedings of the 24th National and 2nd International ISHMT-ASTFE Heat and Mass Transfer Conference (IHMTC-2017)
HEATING LEVELS ON SCRAMJET INTAKE AND COMBUSTOR DUCT
要約
Aerothermal design is a key aspect in design and
development of air breathing scramjet engines. Hypersonic
vehicles in dense atmospheres experience severe aerodynamic
heating at leading edges and intake compression ramps.
Combustor duct walls experience high heating owing to
reflected shock systems and supersonic combustion. ISRO
successfully demonstrated supersonic combustion in flight.
Two scramjet engine modules were attached to the aft end of
second stage of the carrier vehicle. During the flight,
supersonic combustion under regulated fuel supply mode was
achieved. Flight thermal measurements provide valuable
insight on the heating levels experienced at critical regions.
This paper examines the heat flux measurements carried out at intake ramp and combustor regions of the scramjet engine
module during flight. Slug type heat flux sensors were
instrumented with one at inlet ramp and two heat flux sensors in combustor region for both engines. Heat flux was derived from the measured thermal response of the slug gauge. Thermal model of the slug heat flux sensor was also generated to predict slug temperature history for derived heating rates. The measured aerodynamic heat flux at intake ramp is in good agreement with estimated. The measured heat flux inside combustor duct behind struts shows severe heating levels indicating successful combustion during flight.