Experimentally investigation of flame temperature distribution inside a can type combustor

A gas turbine combustor has been investigated experimentally in this paper. The effect of air and fuel flow rates on the on combustor performance and lean blow out at atmospheric and steady condition is the goal. The combustor is a can type with swirl pressure fed injector. An axial swirler with swirl No. equal to 0.8 has been installed. The kerosene has been used as fuel while the air temperature at combustor inlet is equal to 315 K. The combustor Stability loop has been determined with several tests. Then variation of temperature inside the combustor and at combustor exit with respect to the injector back pressure and air flow rate are measured. 4 operating conditions have been selected due to detail investigation of flame temperature contour inside the combustor. The results show that the flame holds near the walls. Also, the pattern factor show that the best condition is when the flame is totally inside the combustor while the air flow rate is minimum. Furthermore, it is cleared that the lean blow out is not uniform. It means that with increasing the air flow rate, upper section of flame has been quenched and then the lower section of flame.