A brief retroversion is conducted on the developments of pulse detonation engines over these decades. Attempts are made to cover performance analysis, nozzle effects, partial filling, and cooperating work. Researchers have spared no effort to establish accurate models to describe the unsteady nature of pulse detonation engines while the accuracy is relatively just as it comes at the price of more or less simplification. Nozzle design would make a great difference to the ultimate performance as numerical simulations have proved nozzle shape, as well as expansion ratio, needs precisely devised. The partial filling has an impact on specific impulses by altering the pressure relaxation process which is testified by numerical simulations and experiments. Component matching brings a challenge to engineering practice due to the comprehensive and complicated co-reaction between every part of the engine. How to reconcile different components remains a fatal issue as many institutes have done amounts of work to demonstrate the feasibility of such a novel propulsion option.
In order to obtain the dynamic operating characteristics of a pulse detonation turbine engine (PDTE), a transient model is established considering the shaft dynamics and the volumetric effect of the components in the PDTE. The accuracy of the model is verified with the experimental data from a pulse detonation prototype engine. The deviations between the calculated data and the experimental results are no more than 7.61%. The numerical results show that the operating state of the PDTE will change gradually with the increase of the fuel flow rate or the firing frequency. The quasi-steady state calculations show that there are maximum values for the rotor speed, thrust, and specific thrust when the fuel flow rate is increased from 0.0056 kg/s to 0.0129 kg/s at firing frequency of 10 Hz. The rotor speed, thrust, and specific thrust will suddenly decrease due to the over rich of fuel in the PDC with the increasing of the fuel flow rate. The specific fuel consumption has a minimize value during this process. When the firing frequency is increased from 7 Hz to 18 Hz at a fixed fuel flow rate, the performance parameters such as the thrust, specific thrust, and specific fuel consumption have a similar variation trend. The extremum values of the performance parameters are obtained at firing frequency of 12 Hz. For the dynamic operating process of the PDTE, parameters such as the rotor speed or pressure ratio of the compressor are increased in a cyclic oscillation way when the fuel flow rate or the firing frequency is changed.
Aiming at the difficulty of numerical simulation of the DDT process during the detonation combustion of aviation kerosene, this paper has presented a single-component simplified mechanism of aviation kerosene to carry out the numerical simulation of the DDT detonation process. By simplifying the detailed mechanism of n-decane, the simplified mechanism of RP-3 aviation kerosene single-component alternative fuel was obtained, and the DDT process of aviation kerosene was numerically simulated, and the influence law of the obstacle blocking ratio and arrangement mode on the DDT process was analyzed. The results show that the simplified mechanism model for the single-component alternative fuel can better fit the combustion characteristics of aviation kerosene under high temperature and pressure. The numerical simulation results of the DDT process are analyzed, and it is found that the DDT time will increase with the increasing of blocking ratio. The DDT time at the same blocking ratio is shorter when the obstacles are symmetrically distributed.
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