Abstract A lean burn gas turbine combustor has a premixer zone receiving compressor discharge air through openings in a combustor liner. A fuel nozzle has an upstream orifice 52, a downstream orifice 56, and a captured response volume 54 therebetween. Upstream orifice 52 affords a high pressure drop for gaseous fuel to approximately the pressure of the compressor discharge air. The low pressure discharge orifice affords a pressure drop comparable to the pressure drop across the openings of the combustor liner for the air supply. The dynamic pressure response characteristics of the fuel and air inlets to the premixer zone are substantially matched to eliminate variations in fuel/air concentration resulting from pressure variations in the premixer zone. The captured response volume between the upstream and downstream orifices is sized sufficiently to store enough fuel to accommodate the mismatch in phase angle of fuel flowing into the captured response volume through the upstream orifice at a first phase angle relative to the phase angle of a pressure forcing function in the premixer zone and fuel flowing out of the captured response volume through the downstream fuel discharge orifice at a second phase angle relative to the phase angle of the pressure forcing function.
Apparatus for stabilizing combustion in a gas turbine combustor operable in a lean premixed mode, and having a premixer zone, comprising: an air supply system including an opening for delivering air into the premixer zone of the combustor and having a predetermined pressure upstream of said opening; a nozzle including a fuel passage for passing fuel into the premixer zone of the combustor; said fuel passage having a discharge orifice for delivering fuel into the premixer zone; and means upstream of said fuel discharge orifice for reducing the fuel pressure upstream of said fuel discharge orifice to approximately said predetermined pressure, said air supply opening and said fuel discharge orifice having substantially the same pressure drop, whereby pressure fluctuations in the premixer zone resulting from fuel/air concentration oscillations are substantially minimized or eliminated.
Claim 2
Dependent Claim
133 words
Apparatus for stabilizing combustion in a gas turbine combustor operable in a lean premixed mode, and having a premixer zone, comprising: an air supply system including an opening for delivering air into the premixer zone of the combustor and having a predetermined pressure upstream of said opening; a nozzle including a fuel passage for passing fuel into the premixer zone of the combustor; said fuel passage having a discharge orifice for delivering fuel into the premixer zone; and means upstream of said fuel discharge orifice for reducing the fuel pressure upstream of said fuel discharge orifice to approximately said predetermined pressure, said air supply opening and said fuel discharge orifice having substantially the same pressure drop, whereby pressure fluctuations in the premixer zone resulting from fuel/air concentration oscillations are substantially minimized or eliminated.
Claim 3
Dependent Claim
18 words
Apparatus according to claim 1 including a volume in said fuel passage upstream of said fuel discharge orifice.
Claim 4
Dependent Claim
129 words
Apparatus according to claim 1 wherein said reducing means includes an orifice in said fuel passage upstream of said fuel discharge orifice, said upstream orifice affording a higher pressure drop than the pressure drop across said fuel discharge orifice and a volume in said fuel passage between said upstream and fuel discharge orifices at substantially the same pressure as said predetermined pressure and sized sufficiently to store enough fuel to accommodate any mismatch in phase angle of fuel flowing into said volume through said upstream orifice at a first phase angle relative to the phase angle of any pressure fluctuation in the premixer zone and fuel flowing out of said volume through said discharge orifice at a second phase angle relative to the phase angle of the pressure fluctuation.