Abstract
The numerical simulation and direct-connection experiments were carried out to investigate the impact of the variation of injection schemes on the combustion performance of axisymmetric RBCC combustor with different configurations in scramjet mode, in which the strut-rocket was used as the means of ignition source and flameholding and the fuel was injected from the fuel-pylon. The results and their analysis indicated that: (1) the combustor performance upgraded gradually as the quantity of fuel-pylon injection increased in the manner of fuel-pylon injection with wall injection; (2) compared with the scheme of fuel injection of fuel-pylon and wall, the combination of fuel-pylon injection with central strut injection achieved higher combustion performance; (3) the joint of fuel-pylon with cavity could promote combustion and could get better combustion performance; thus the inner thrust is 1.1 times as the thrust of fuel-pylon with rearward facing step; (4) the increase in the height of fuel-pylon enhanced the combustion organization between fuel and air while the thrust generated by combustor could offset the resistance loss of pylon completely.
| Original language | English |
|---|---|
| Pages (from-to) | 29-34 |
| Number of pages | 6 |
| Journal | Xibei Gongye Daxue Xuebao/Journal of Northwestern Polytechnical University |
| Volume | 32 |
| Issue number | 1 |
| State | Published - Feb 2014 |
Keywords
- Axisymmetric
- Carbon dioxide
- Combustion
- Combustion performance
- Combustors
- Computer simulation
- Experiments
- Fuels
- Ignition
- Mach number
- Oxygen
- Pressure
- Pressure distribution
- Ramjet engines
- RBCC
- Rockets
- Schematic diagrams
- Scramjet mode
- Temperature distribution