| Citation: | WU Jun, CHEN Minmin, CHEN Xiang, et al. Design and experiment of grand scale diameter and small annular cavity combustor[J]. Journal of Aerospace Power, 2023, 38（11）：2711-2717 doi: 10.13224/j.cnki.jasp.20220115
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Design and experiment study of a grand scale diameter and small annular cavity combustor were carried out for the first time interiorly, considering the turbine engine with innovated structure. A combustor design scheme based on annular vortex field matching tangential fuel injection under the condition of diffuser with reverse air intake was proposed. Cold and hot performance experiments of combustor under different conditions were carried out, the combustor characteristics including flow resistance characteristics, ignition characteristics at ambient temperature and pressure, lean blow out characteristics, combustion efficiency, as well as the outlet temperature field, were obtained. The results showed that: （1） the design scheme met the design requirements of combustor; （2） compared with conventional combustor, the nozzle spacing ratio of the scheme reached 1.65; （3） the ignition performance of the designed combustor was excellent, as its minimum lean ignition fuel-air-ratio reached 0.016 and its ignition and flame combination time was within 4 s; （4） the total pressure loss, combustion efficiency, out temperature distribution factor （OTDF） and radial temperature distribution factor （RTDF） of the designed combustor had outstanding performance; as the combustion efficiency of idle state reached 98.6%, the OTDF of design point reached 0.16 as well.
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