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The RACC system uses fifth-stage compressor bleed air that has been modulated
according to the N2 and the flight parameters. The bleed air goes to the N~3 bearing
compartment, where it is mixed with fan boost discharge.
Clearances are at the maximum when the RACC valve is closed.
CCM ALL
┏━━━━━━━━━━━━━━━━┳━━━━━━━━━━━━━━┳━━━━━━━━━━━┓
┃ ┃ ┃1.70.60 P 2 ┃
┃ ┃ ┣━━━━━┳━━━━━┫
┃I ~-~ A318 ┃l POAIRBLEEDTSYSTEM ┃SEQ 005 1 ┃I REV 23 ┃
┃ aw aw ,, ~L,~ .4319 ┃ ┃ ┃ ┃
┃ Lli,~ A320 ┃ ┃ ┃ ┃
┃ A~7-~'M" A321 ┃ ┃ ┃ ┃
┃ FLIGHT CREW OPERATING MANUAL ┃ ┃ ┃ ┃
┗━━━━━━━━━━━━━━━━┻━━━━━━━━━━━━━━┻━━━━━┻━━━━━┛
HP TURBINE CLEARANCE CONTROL (HPTCC) SYSTEM
The FADEC controls the HPTCC system through the HMU. The HPTCC system controls the
HP turbine clearance by modulating the HP compressor bleed air flow for cooling the HP
turbine case.
It optimizes HP turbine performance and reduces exhaust gas temperature.
LP TURBINE CLEARANCE CONTROL (LPTCC) SYSTEM
The FADEC controls the LPTCC system through the HMU. The LPTCC system controls LP
turbine clearance by modulating the fan bleed air flow for cooling the LP turbine case.
┏━━━━━━━━━━━━━━━━┳━━━━━━━━━━━━┳━━━━━━━━━━━┓
┃J -~ A318 ┃ POWER PLANT ┃1.70.70 P 1 ┃
┃ .*,,.8, ,, ~L,~ A319 ┃ ┃ ┃
┃ ┃ ┣━━━━━┳━━━━━┫
┃ Lli,~ A320 ┃ ┃SEQ 005 J ┃J REV 23 ┃
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本文链接地址：
AIRBUS A320 Flight Crew Operating Manual5(166)
