Semi-closed cycle aero engine with contrail suppression
OwnerWilliam E. Learinventor
Life of this patent
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Abstract
Various embodiments relate to a system and method of suppressing contrails emitted from an aircraft. One such system comprises a semi-closed cycle gas turbine engine of an aircraft that exhausts gases in use; a recuperator component that is positioned within an exhaust gas stream of the semi-closed cycle gas turbine engine to remove a portion of the exhaust gas stream in a form of heat energy; and one or more additional heat exchangers in a recirculation path that are configured to condense the heat energy of the portion of the exhaust gas to remove water vapor from the exhaust gas stream. Other systems and methods are also provided.
Claims15
A system of suppressing contrails emitted from an aircraft comprising:
- a semi-closed cycle gas turbine engine of an aircraft that exhausts gases in use;
- a recuperator component that is positioned within an exhaust gas stream of the semi-closed cycle gas turbine engine to remove a portion of the exhaust gas stream in a form of heat energy;
- and
- one or more additional heat exchangers in a recirculation path that are configured to condense the heat energy of the portion of the exhaust gas to remove water vapor from the exhaust gas stream.
A method of suppressing contrails emitted from an aircraft comprising:
- providing a semi-closed cycle gas turbine engine of an aircraft that exhausts gases in use;
- removing, via a recuperator component, a portion of the exhaust gas stream in a form of heat energy;
- receiving, via one or more additional heat exchangers in a recirculation path, the removed exhaust gas stream;
- condensing the heat energy of the removed exhaust gas stream to form liquid water;
- and
- internally storing the liquid water thereby suppressing a formation of contrails emitted from the aircraft via the exhaust gas stream.
Dependencies are inferred from the claim text.