| 主权项 |
1. An aircraft engine, comprising:
a nacelle with an air inlet and an air outlet; a cavity defined within the nacelle, the cavity permitting ambient air to pass through the nacelle from the air inlet to the air outlet; an inner fixed structure dividing the cavity into an engine core compartment and a fan bypass channel; a compressor region defined within the engine core compartment, the compressor region producing bleed air taken from at least one position between the air inlet and the air outlet; a precooler disposed within the nacelle, the precooler defining an ambient air passage and a bleed air passage, wherein the ambient air passes to the engine core compartment through the ambient air passage from an ambient air inlet to an ambient air outlet, wherein the bleed air passes through the bleed air passage from a bleed air inlet to a bleed air outlet, and wherein heat is transferred between the ambient air and the bleed air via heat exchange within the precooler; at least one pressure relief door disposed on the inner fixed structure to create additional engine venting through the pressure relief door, when opened; and a controller operatively connected to the pressure relief door, wherein the controller at least opens the pressure relief door based on a demand for increased flow of the ambient air through the ambient air passage. |
