Appeal No. 2003-0304
Application 09/703,302
compressor means (3, 4); a turbine (6, 7) driven by expanding a
gaseous material (e.g., fuel or oxidizer) operatively associated
with the means for compressing; and means (1) operatively
associated with the gas duct for exhausting gases from the gas
duct.
Independent claim 16 on appeal is readable on the engine of
Figure 1 of Mirville in the following manner, noting particularly
that the engine of Figure 1 in Mirville is a rocket engine
capable of serving as a gaseous-fuel breathing engine, and
comprises a gas duct (11) defining an intake capable of handling
a gaseous fuel; a compressor (3, 4) disposed axially within the
gas duct for compressing any gas within the duct, including a
gaseous fuel; one or more injectors (17) for injecting a gaseous
material (e.g., fuel or oxidizer) into the compressed gas flow
downstream of the compressor (3, 4); a turbine (6, 7) operatively
associated with the compressor for driving the compressor,
wherein the turbine is driven by expanding a gaseous material
(e.g., fuel or oxidizer); and one or more nozzles (1) operatively
associated with the gas duct for exhausting gases from the gas
duct.
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