| 摘要 |
<p>An annular combustor system (10) is disclosed in use with a radial turbine-type gas turbine engine module (12), the system (10) having an annular housing (40) defining a single stage combustor, an external fuel/air premixer system (60) having a mixing chamber (68) and a compressed air valve (90) and a fuel valve (92) both under the control of a controller (94), to provide a preselected lean fuel/air ratio mixture for introduction to the combustion zone (54) of the annular housing (40). Compressed air conduits (80) are used to channel a portion of the total compressed air flow to the premixer (60) and the remainder to the dilution zone (56) of the combustor (10), and a fuel conduit (66) is used to deliver all of the fuel to the premixer (60). Convection cooling of the annular housing (40) is accomplished using compressed air without diluting the fuel air ratio in the combustion zone (54). The premixer (60) includes a venturi (68), a fuel nozzle (64) for spraying fuel into the venturi inlet (70) along the venturi axis (74), and a premixer housing (62) integrating the compressed air valve (90), the venturi axis (74) being aligned substantially tangentially to the annular housing axis (42) to provide a swirling admission of the premixed fuel/air mixture to the combustion zone (54). <IMAGE></p> |
