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http://dx.doi.org/10.6108/KSPE.2018.22.3.001

Combustion Test for a Supersonic Combustor Using a Direct-Connected Facility  

Yang, Inyoung (Engine System Research Team, Korea Aerospace Research Institute)
Lee, Kyung-Jae (Engine System Research Team, Korea Aerospace Research Institute)
Lee, Yang-Ji (Engine System Research Team, Korea Aerospace Research Institute)
Lee, Sanghoon (Engine System Research Team, Korea Aerospace Research Institute)
Kim, Hyungmo (Engine Component Research Team, Korea Aerospace Research Institute)
Park, Poomin (Engine Component Research Team, Korea Aerospace Research Institute)
Publication Information
Journal of the Korean Society of Propulsion Engineers / v.22, no.3, 2018 , pp. 1-7 More about this Journal
Abstract
A combustion test for a supersonic combustor was conducted using a direct-connected type supersonic combustor test facility. The facility was verified for the capability of simulating required flow conditions. The test condition was maintained at Mach 2.0, $915^{\circ}C$ and 496 kPa for 15 s. Using gaseous hydrogen as the fuel, the combustor model was also tested for its ignition and flame holding capability at the fuel equivalence ratio of 0.12. Combustion efficiency was 71%, and the supersonic flow regime was obtained at this test condition.
Keywords
Supersonic Combustor; Scramjet; Hypersonic Air-breathing Engine; Direct-connected Test Facility;
Citations & Related Records
Times Cited By KSCI : 2  (Citation Analysis)
연도 인용수 순위
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