GAS TURBINE ENGINE AND METHOD TO COOL A GAS TURBINE ENGINE CASE ASSEMBLY

GAS TURBINE ENGINE AND METHOD TO COOL A GAS TURBINE ENGINE CASE ASSEMBLY

A method of cooling a gas turbine engine case assembly includes moving a fan air valve (62) that is operatively connected to a pre-cooler (64) having a bypass inlet (70) that is configured to receive bypass air that bypasses a gas turbine engine core to facilitate a provision of bypass air through a...

Ausführliche Beschreibung

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Bibliographische Detailangaben
Hauptverfasser: RIORDAN, William J, EVETTS, Joseph D, PAPA, Federico
Format: Patent
Sprache:eng ; fre ; ger
Schlagworte:
AIR INTAKES FOR JET-PROPULSION PLANTS
BLASTING
COMBUSTION ENGINES
CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
GAS-TURBINE PLANTS
HEATING
HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
LIGHTING
MECHANICAL ENGINEERING
WEAPONS
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Beschreibung
Zusammenfassung:A method of cooling a gas turbine engine case assembly includes moving a fan air valve (62) that is operatively connected to a pre-cooler (64) having a bypass inlet (70) 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 (60) to the bypass inlet to a first open position, in response to a core compartment (34) temperature being greater than a target core compartment temperature. The method further includes bleeding the bypass air through a bypass outlet (72) of the pre-cooler into a core compartment.