A method of cooling a gas turbine engine case assembly includes moving a fan air valve that is operatively connected to a precooler having a bypass inlet that is configured to receive bypass air that bypasses a gas turbine engine core to facilitate a provision of bypass air through a fan air valve inlet to the bypass inlet to a first open position, in response to a core compartment temperature being greater than a target core compartment temperature. The method further includes bleeding the bypass air through a bypass outlet of the precooler into a core compartment.
Gas turbine engine and method to cool a gas turbine engine case assembly
2020-04-14
Patent
Electronic Resource
English
Gas turbine engine and method to cool a gas turbine engine case assembly
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