According to the interstage turbine burner(ITB)operation condition

an ITB annular combustor test rig

which used trap vertex combustor design

was designed and manufactured based on ITB being used in a certain turbo-shaft engine

and combustor performance experiment study was performed. The results show that: the lower flammable limit of the ITB is 10.2

and it is favorable to ignite when the pressure difference between the inner of the cavity and the outer of the cavity is reduced. As compared with the ordinary combustor

the combustion efficiency of the ITB is lower

and the combustion efficiency improves when the inlet temperature increases. The total pressure recovery coefficient of the ITB is lower

and the variation of inlet temperature has a less effect on the pressure recovery coefficient. The outlet temperature distribution factor(OTDF) is good

and the outlet temperature distribution factor decreases when the inlet temperature increases. When the inlet temperature increases

the wall temperature of the liner would be partially higher

and the cooling design of the liner should be optimized.