Abstract
Sudden extinction of a microturbojet engine combustor was encountered during the engine accelerating process, which motivates the present work to optimize the combustor performance. Numerical results show that by decreasing the primary zone air-introducing area and increasing the dilution zone air-introducing area, the primary zone air percentage is reduced from 39.35% to 32%, and the primary zone excess air ratio is reduced from 1.122 to 0.915, which is believed to be beneficial for flame stability both in terms of residence time and rich burn. Meanwhile, the vortex flow pattern in the primary zone varies little as the variations of the airflow distribution. The new engine, which is equipped with the optimized combustor, is tested by experiments. The successful accelerating to the rotating design speed demonstrates the effectiveness of combustor optimization work.
Highlights
Microturbojet engine combustor features small size, high heat capacity, the short residence time of fuel, and flame stabilizing problem in the full speed range, which makes it a bottleneck in microturbojet engine development [1, 2]
Huang et al [8, 9] proposed a convenient criterion to assess if the design of a microturbojet engine can generate thrust; recent development and key techniques of microturbojet engine of the centimeter size were discussed
In the following research process, sudden combustor extinction happens when rotating speed is at 80% of design speed
Summary
Microturbojet engine combustor features small size, high heat capacity, the short residence time of fuel, and flame stabilizing problem in the full speed range, which makes it a bottleneck in microturbojet engine development [1, 2]. Some public researches focus on conventional annular combustor of small and medium size [6, 7] This combustors’ design is of limited value to the design of microturbojet engine combustors, with considerations of their difference in size and heat capacity. Huang et al [10, 11] worked on an annular combustion chamber with centrifugal fuel injection and the structure design of a high power density microturbojet engine of 100 N thrust and 105 r/min rotational speed. This paper provides the preliminary design of the combustor and describes the phenomena and data of the sudden extinction during the engine accelerating process. At last, this problem is solved successfully by the optimization of the combustor. The presented work is of some reference value both at the scientific and engineering levels
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