Difficulties in achieving reliable starts in gas turbine engines operating at high altitude are avoided in a gas turbine engine including a rotary compressor (10), a rotary turbine wheel (12) coupled to the compressor (10) to drive the same, and a nozzle (42) for directing gases of combustion against the turbine wheel (12). An annular combustor (34) has an outlet (40) connected to the nozzle (42) and an opposed dome (38) that is axially spaced from the outlet (40). At least three sets of air injection openings (80, 92, 100) are axially spaced from one an...
A gas turbine engine comprising: a rotary compressor; a rotary turbine wheel coupled to said compressor to drive the same; a nozzle for directing gases of combustion against said turbine wheel; an annular combustor having an outlet connected to said nozzle and an opposed dome axially spaced from said outlet; at least three sets of air injector openings, each set axially spaced from one another with one set in close proximity to said dome; fuel injectors associated with two of said sets including said one set and the other of said sets that is nearest sai...
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