| CPC F23R 3/40 (2013.01) [F02C 3/20 (2013.01)] | 15 Claims |
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1. A gas turbine engine assembly for an aircraft, the gas turbine engine assembly comprising:
a gas turbine engine including:
a cold pre-combustion section;
a combustion section configured to combust jet fuel to generate combustion gases;
a hot post-combustion section including rotating turbine blades and stator blades;
a catalyst in the hot post-combustion section and configured to convert nitrogen oxides in the combustion gases flowing along a flow path through the hot post-combustion section into diatomic nitrogen and water in presence of an exhaust fluid additive; and
at least one outlet in one or more of the stator blades, wherein the at least one outlet is configured to inject exhaust fluid additive upstream of the catalyst in the flow path, and the one or more stator blades with the at least one outlet are between a plurality of the rotating turbine blades;
wherein the exhaust fluid additive has a different composition than the jet fuel,
wherein the exhaust fluid additive is configured to react, in the presence of the catalyst, with the nitric oxides (NOx) in the combustion gases flowing through the hot post-combustion section, and
a tank system configured to contain the a tank system configured to contain the exhaust fluid additive which is supplied to exhaust fluid additive which is supplied to the at least one outlet, wherein the tank system is in a wing of the aircraft or in a pylon between the wing and the gas turbine engine.
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