CPC F02C 7/14 (2013.01) [F05D 2220/323 (2013.01); F05D 2260/213 (2013.01); F05D 2270/303 (2013.01); F05D 2300/50212 (2013.01)] | 20 Claims |
1. An aircraft engine, comprising:
a core gas path through which a core gas flow flows;
an exhaust duct receiving the core gas flow;
an air-cooled heat exchanger disposed in a heat exchanger duct having an air inlet providing cooling air to the air-cooled heat exchanger and an air outlet in fluid communication with the exhaust duct; and
a cover disposed in the heat exchanger duct downstream of the air-cooled heat exchanger, the cover movable between an open position, in which the cover allows the cooling air to flow through the air outlet into the exhaust duct, and a closed position, in which the cover substantially blocks the air outlet, wherein the cover is operable to move from the open position to the closed position at a predetermined temperature of the cover.
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