Ignition Delay in solid-fuel ramjet combustor

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The ignition delay requirement and ignition characteristics of a solid fuel in the ramjet combustor were investigated. The shock in a simple diffuser geometry was calculated to obtain the upper limit of ignition delay, and it was determined to be shorter than 1 s. To achieve this short ignition delay, a high-density polyethylene (HDPE) fuel grain coated with an ignition support material and a fuel-rich propellant (FRP) were prepared. The ignition support materials were nitrocellulose with boron potassium nitrate (NC/BKNO3) and an ammonium perchlorate (AP)/hydroxyl-terminated polybutadiene (HTPB)-based composite propellant. For testing purposes, a compact gas generator was built to simulate the conditions in the ramjet combustor. The simulation results revealed that the NC/BKNO3 ignition support material showed the shortest ignition delay of 1.27 s, but the flame in this case was not sufficient to ignite the HDPE. In a demonstration test, an ignition support material composed of NC/BKNO3 and the AP/HTPB-based composite propellant was applied to the FRP fuel grain, in which case a stably sustained flame was obtained. The test results demonstrated that ignition of the FRP and that of the ignition support material occurred simultaneously with an ignition delay of 1.74 s.
Publisher
AMER INST AERONAUTICS ASTRONAUTICS
Issue Date
2018-11
Language
English
Article Type
Article; Proceedings Paper
Citation

JOURNAL OF PROPULSION AND POWER, v.34, no.6, pp.1519 - 1528

ISSN
0748-4658
DOI
10.2514/1.B36955
URI
http://hdl.handle.net/10203/247130
Appears in Collection
AE-Journal Papers(저널논문)
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