Study of Flow Field Inside a Can Combustor for Micro Gas Turbine Engine Under Nonreacting Flow Conditions

نویسندگان

چکیده

Generally, micro gas turbines are in the range of 15 to 300 kW. However, recent applications unmanned aerial vehicles (UAVs) and polygeneration require a small turbine. So, here swirl combustor designed for turbine engine capacity less than 1 kW is analyzed under nonreacting flow conditions. Simulations have been carried out study field inside can combustor. Flow characteristics, like velocity, path lines, turbulent intensity total pressure loss studied. The across also measured experimentally compared with that simulation results. Good agreement achieved between experimental numerical drop was found be negligible 0.002 0.06% at an inlet velocity ranges from 1.7 10.19 m/s. pattern indicates strong swirling interaction secondary air entrainment flame tube.

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ژورنال

عنوان ژورنال: Journal of Aerospace Technology and Management

سال: 2021

ISSN: ['2175-9146', '1984-9648']

DOI: https://doi.org/10.1590/jatm.v13.1185