design and experimental investigation of RBCC engine operating from Mach 2.0 to 6.0
- Paper number
IAC-14,C4,P,50,x23877
- Author
Mr. Chunqin Luo, Science and Technology on Scramjet Laboratory, Beijing Power Machinery Research Institute, China
- Coauthor
Dr. Baoxi Wei, Science and Technology on Scramjet Laboratory, Beijing Power Machinery Research Institute, China
- Coauthor
Dr. Feiteng Luo, Science and Technology on Scramjet Laboratory, Beijing Power Machinery Research Institute, China
- Coauthor
Mr. Xin Ren, Science and Technology on Scramjet Laboratory, The 31st Research Institute of CASIC, China
- Coauthor
Mr. Zhuang Ning, Science and Technology on Scramjet Laboratory, Beijing Power Machinery Research Institute, China
- Coauthor
Dr. Qiang Gang, Science and Technology on Scramjet Laboratory, Beijing Power Machinery Research Institute, China
- Year
2014
- Abstract
Rocket Based Combined Cycle(RBCC) engine can be designed by several different types to adapt different application missions, which integrates rocket and ramjet or scramjet. A RBCC engine flowpath model operating from Mach 2.0 to 6.0 flight condition is designed, that mainly works at ramjet mode and rocket-ramjet mode. Such type of RBCC engine has merits with easiness to design and relatively high reliability, because the mature design method for ramjet can be referenced. A series of direct-connect tests were conducted on the designed RBCC engine model at Mach 2.0, Mach 4.0 and Mach 6.0 conditions. In all tests, gaseous oxygen and liquid kerosene are used for the rocket thruster, with nominal total pressure and O/F ratio fixed at 2.0MPa and 1.6 respectively. Reliable ignition and steady combustion realized under all test modes. Performance of ramjet mode and rocket-ramjet mode were carefully investigated by analyzing test data. Test results indicate that rocket jet and total equivalence ratio in ramjet combustor have important effects on RBCC engine.
- Abstract document
- Manuscript document
IAC-14,C4,P,50,x23877.pdf (🔒 authorized access only).
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