Abstract
As a part of the NEDO project "Development of the Palm top gas turbine", we have been developing the annular type propane-fueled combustor for the gas turbine. To specify the combustor inlet structure, the combustion characteristics in a can-type test combustor have been studied by varying the following parameters; the throat diameter of an air inlet nozzle and the hole number and diameter of a fuel injector. At the design point of the combustor, a propane-air flame was stabilized in the chamber length of 100 [mm]. Space heating ratio of the combustor is 180 [MW/m^3/Mpa]. The combination of the fuel injector with a wide interval of holes and the air inlet nozzle with a large throat diameter was excellent in the flame stability and the combustion efficiency. The annular-type actual combustor for the 3-kW output gas turbine was designed to satisfy the performance of the gas turbine.
