GE-CF6-80E1-95

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BORE COOLING
VALVE (3 PLACES)
LOW PRESSURE
TURBINE CASE
COOLING
(BIRDCAGE)
HIGH PRESSURE
TURBINE CASE
COOLING HPT CLEARANCE
CONTROL VALVE
FAN DISCHARGE
AIR SOURCE
HEAT SHIELD COOLING
IGNITION LEADS AND
RIGHT SIDE
A330 - ENGINE ATA 71 up 80
GE CF6-80E1 189 of 394
 
 
 
 
 
 
 
 
 
 
 
BORE COOLING SYSTEM
Bore Cooling System Description
In the fan frame inner strut area, five openings are located on the forward edge
for air removal. These openings pressurize the B/C sump cavity via external
engine tubing and supply bore cooling air to the core compressor rotor. Bore
cooling flow from one of these ports is controlled by an exterior mounted valve.
The other four ports maintains constant flow.
The core compressor rotor bore temperature calculated by the ECU and the
engine power setting determine the bore cooling valve opening.
Bore cooling demand is based on corrected core speed (N2K), T3 and T25.
The bore cooling valve is mounted to the aft fan case at the 5:30 o’clock
position aft looking forward. The valve is a two position sleeve type valve
actuated by an attached solenoid. The valve contains two electrical connectors
that interface it directly with the ECU. The valve saves primary air by reducing
the cooling airflow to the center bore of the engine during low power
operations.
Booster discharge air removed by leading edge openings on five of the fan
frame struts supplies the cooling flow. Air removed by four of the struts is
routed directly to the center bore. Air removed by the other strut is first piped to
the bore cooling valve, then routed to the center bore. The cooling airflow is
reduced by closing the bore cooling valve.
A330 - ENGINE ATA 71 up 80
GE CF6-80E1 190 of 394