Abstract
A simplified single channel wave rotor combustor (WRC) experimental rig was established, in which the spoilers with different blockage ratios (BR) could be conveniently installed and disassembled. The spoilers were firstly used for WRC to improve the pressure rise. The effects of different blockage ratios on the pressure rise and flame acceleration characteristics in a single channel of the WRC were investigated. The addition of spoilers could remarkably improve the pressure rise and flame propagation speed in a single channel of the WRC. While the blockage ratio of the spoiler increases, both pressure rise and mean flame propagation speed are improved. When the spoilers with a blockage ratio of 38.91% are used, the peak pressure increases by 200% compared to that of WRC without the spoilers. When the spoilers of different blockage ratios (23.35%, 31.13%, and 38.91%) are used, it is found that the flame propagation speed is significantly improved with the increasing of the blockage ratio. Specifically, the maximum flame propagation speed reaches 55 m/s, and the maximum mean flame propagation speed is 36.95 m/s. Furthermore, combustion becomes more intense, and the flame is brighter around the spoiler.
Highlights
For a gas turbine engine, pressure gain combustion has a strong potential to significantly improve the performance and reduce emissions [1]
The results revealed that deflagration-todetonation transition (DDT) can only be achieved when the flame propagation speed is increased to half of the propagation speed of the ChapmanJouguet detonation wave, while a blockage ratios (BR) of 0.3~0.6 can effectively accelerate the propagation of flames
As the flame propagation accelerates, the pressure wave peak is seen to be closer to the flame, and the two values are almost coupled at ion probe 3 (IP3) and pressure transducer 3 (PT3), almost generating detonation combustion
Summary
For a gas turbine engine, pressure gain combustion has a strong potential to significantly improve the performance and reduce emissions [1]. Wave rotor combustor (WRC) is an unsteady pressure gain combustion device [5,6,7]. The channel is mostly filled with some combustible mixture Both the inlet and outlet close; the hot jet gas enters the channel to ignite the International Journal of Aerospace Engineering. The outlet duct closes and the inlet remains open, and hammer shock waves are produced at the outlet This process is referred to the precompression process of the WRC. Matsutomi et al investigated the combustion characteristics of a WRC with an air flow rate of 9.6 lbm/s, an acetylene flow rate of 0.51 lbm/s, and a wave rotor speed of 2100 rpm, and variation of the total pressure was measured at both the inlet and the outlet [14]. Chinnathambi et al established a singlechannel WRC experimental rig to explore the effects of different fuels on ignition and flame propagation processes while neglecting filling and discharge of the gas mixture in
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