Synthesizing the several partial studies on the air-craft gasturbine combustor, a basic design method of combustor is established.
Combustion experiment has been carried out to verify the design method of flame tube liner port. Exit temperature uniformity was investigated and the concentrations of $CO_2$, CO and $O_2$ were measured by ORSAT gas analyser for the five models which have different liner size and distribution.
From the results of experiment, it is found that the established method will be useful for basic design of aircraft gas turbine combustor.
