DOC AIRBUS | AMM A320FHP COMPRESSOR SECTION - DESCRIPTION AND OPERATION
** ON A/C NOT FOR ALL
1. General
The major components of the compressor are : compressor rotor and compressor stator. The front of the compressor stator is supported by the fan frame and the front of the compressor rotor is supported by the No.3 bearing in the fan frame. The rear of the compressor stator is attached to the combustion case and the rear of the compressor rotor is attached to the HPT rotor to form the core rotor. The rear of the core rotor is supported by the No.4 bearing. A portion of the fan discharge airflow passes thru the booster to the compressor. Compression is progressive as the primary airflow moves from stage through the axial compressor.
Air passes through successive stages of compressor rotor blades and compressor stator vanes, being compressed as it passes from stage to stage. After passing through 9 stages of blades, the air has been compressed.
The inlet guide vanes and the first 3 stages of the stator are variable, and change their angular position as a function of compressor inlet temperature and engine speed. The purpose of this variability is to optimize efficiency and stall margin for engine speed, compressor inlet temperature and pressure conditions.
The major components of the compressor are : compressor rotor and compressor stator. The front of the compressor stator is supported by the fan frame and the front of the compressor rotor is supported by the No.3 bearing in the fan frame. The rear of the compressor stator is attached to the combustion case and the rear of the compressor rotor is attached to the HPT rotor to form the core rotor. The rear of the core rotor is supported by the No.4 bearing. A portion of the fan discharge airflow passes thru the booster to the compressor. Compression is progressive as the primary airflow moves from stage through the axial compressor.
HP Compressor SectionAir passes through successive stages of compressor rotor blades and compressor stator vanes, being compressed as it passes from stage to stage. After passing through 9 stages of blades, the air has been compressed.
The inlet guide vanes and the first 3 stages of the stator are variable, and change their angular position as a function of compressor inlet temperature and engine speed. The purpose of this variability is to optimize efficiency and stall margin for engine speed, compressor inlet temperature and pressure conditions.