JPS5741507A - Combustor for gas turbine - Google Patents

Abstract

PURPOSE: To achieve low-NOx combustion of fuel in a combustor of a gas turbine, by providing a passage for feeding cooling air to be supplied to a mixing region after cooling the side face of the combustor and a passage for feeding diluting air to be supplied to a downstream portion of a combustion region, and keeping the mixing ratio of the mixture of fuel and air constant over the entire load range.

CONSTITUTION: Fuel 101 is carried via a fuel pipe 102 and ejected into a first mixing region 120 from a nozzle 103, while high-pressure air is supplied from casing 104 to a bell mouth 106 at the inlet of combustor 105 and to many small apertures 107. Air introduced from the bell mouth 106 is supplied as primary air 1 to the first mixing region 120 via a passage 108, as secondary air 2 to a second mixing region 121 via a passage 109, and as diluting air 2 to a downstream portion of a combustion region 118 via an annular portion 111 and a plurality of pipes 112, respectively. On the other hand, air introduced from apertures 107 is supplied as cooling air 4 to a third mixing region 122 via an annular portion 115. With such an arrangement, mixture of fuel and air pre-mixed sufficiently in the first to the third mixing regions 120 122 is ejected from injection nozzles 123 into the combustion region 118 for combustion therein.

COPYRIGHT: (C)1982,JPO&Japio