Appeal No. 2001-1628 Page 2
Application No. 09/054,794
THE INVENTION
The appellant's invention relates to a fuel-air mixer for a combustor of a gas
turbine engine and more particularly to a means of reducing the formation of carbon
resin on such a fuel-air mixer (specification, p. 1). Claims 1 and 4, the only
independent claims on appeal, read as follows:
1. A fuel-air mixer for a combustor of a gas turbine engine having a
compressor for discharging compressed air to said combustor, said fuel-air mixer
comprising:
(a) a substantially annular venturi defined by a wall having an inner
surface and a longitudinal axis therethrough, said venturi including an upstream
end and a downstream end;
(b) a primary swirler comprising a substantially annular upstream end and
a downstream end located adjacent the upstream end of said venturi along the
longitudinal axis, a plurality of primary air jets interposed between the swirler
upstream and downstream ends, and primary swirler jet airflow supplied to said
primary air jets wherein said swirler airflow is swirled and delivered to said
venturi; and
(c) a fuel nozzle positioned inside the upstream end of said primary swirler
adjacent to said venturi and along the longitudinal axis thereof, said fuel nozzle
further comprising a fuel passage therein through which fuel is sprayed into said
venturi at a designated spray angle; and an air passage therein through which
purge airflow is discharged into said venturi, substantially parallel to the
longitudinal axis of said venturi; wherein said purge airflow is sufficient to provide
a boundary layer of air along the inner surface of said venturi wall.
4. A combustor for a gas turbine engine having a compressor for discharging
compressed air to said combustor, said combustor including a plurality of fuel-air
mixers wherein each said fuel-air mixer comprises:
(a) a substantially annular venturi defined by a wall having an inner
surface and a longitudinal axis therethrough, said venturi including an upstream
end and a downstream end;
(b) a primary swirler comprising a substantially annular upstream end and
a downstream end located adjacent the upstream end of said venturi along the
longitudinal axis, a plurality of primary air jets interposed between the swirler
upstream and downstream ends, and primary swirler jet airflow supplied to said
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