| Citation: | MIAO Junjie, CAI Yiwen, WANG Dong, et al. Optimum design method oriented thrust for over-under TBCC combined nozzle[J]. Journal of Aerospace Power, 2023, 38（6）：1367-1377 doi: 10.13224/j.cnki.jasp.20220883
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Considering the requirements on integration of aircraft/engines, a design method of over-under turbine based combined cycle engine (TBCC) nozzle oriented thrust optimization under a given geometric constraint was proposed. The optimal allocation of the area expansion ratio of the turbo-engine/ramjet nozzle at under-expansion and over-expansion state was realized by means of theoretical analysis and numerical simulation. Within the range of turbo-engine/ramjet pressure-drop-ratio, the TBCC nozzle designed for thrust optimization can achieve higher thrust performance than the baseline nozzle, and the difference in composite thrust coefficient was particularly obvious under the over-expansion state, where the thrust coefficients at Mach number of 0.2 and 3 can be increased by 4.89% and 4.14%, respectively, through thrust optimization. Furthermore, the lift force and pitching moment of thrust optimization nozzle changing with the Mach number were 33% and 47.3% smaller than those of the baseline nozzle, which can effectively reduce the range of aerodynamic focus of the whole aircraft, helping to reduce the trim resistance of wide-speed-range aircraft and the difficulty of flight control.
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