To estimate the effects of incoming flow total temperatures on mode transition boundary in a kerosene-fueled dual mode combustor

an test study was conducted using a direct-connected methane combustion heating test facility. The values of incoming flow total pressure at the isolator inlet should be kept at 1.05 MPa

the Mach number was about 2.0

the incoming flow total temperatures were 885

1 085

1 285 K

respectively. Combustor wall pressures were measured by pressure sensors; the mode of combustion was identified by calculating the Mach number at the isolator exit using a one-dimensional model. Test results indicated that

the locations of the combustor peak wall pressure were the same at different incoming flow total temperatures; there was a one-to-one relationship between the combustor peak pressure value

isolator near wall pressure distribution and shock train leading edge location; with the increase of incoming flow total temperature

the equivalence ratio of mode transition from supersonic to subsonic combustion rose up; under the same kerosene equivalence ratio

as the incoming flow total temperature increased

the combustor wall pressure dropped

the length of shock train got shorter.