DOC AIRBUS | AMM A320FENGINE - GENERAL - DESCRIPTION AND OPERATION
** ON A/C NOT FOR ALL
1. General
The engine is a two spool, axial flow, high bypass ratio turbofan engine. Its compression system features a single stage fan, a four stage booster, and a ten stage High Pressure Compressor (HPC). The Low Pressure Compressor (LPC) is driven by a five stage Low Pressure Turbine (LPT) and the HPC by a two stage High Pressure Turbine (HPT). The HPT also drives a gearbox which, in turn, drives the engine and aircraft mounted accessories.
The two shafts are supported by five main bearings.
The engine incorporates a full authority digital Electronic Engine Control (EEC). The control system governs all engine functions, including power management. Reverse thrust for braking the aircraft after landing is supplied by an integrated system which acts on the fan discharge airflow. Borescope accesses are provided for inspection purposes.
** ON A/C NOT FOR ALL The engine is a two spool, axial flow, high bypass ratio turbofan engine. Its compression system features a single stage fan, a four stage booster, and a ten stage High Pressure Compressor (HPC). The Low Pressure Compressor (LPC) is driven by a five stage Low Pressure Turbine (LPT) and the HPC by a two stage High Pressure Turbine (HPT). The HPT also drives a gearbox which, in turn, drives the engine and aircraft mounted accessories.
Engine BearingsThe two shafts are supported by five main bearings.
The engine incorporates a full authority digital Electronic Engine Control (EEC). The control system governs all engine functions, including power management. Reverse thrust for braking the aircraft after landing is supplied by an integrated system which acts on the fan discharge airflow. Borescope accesses are provided for inspection purposes.
2. Component Location
** ON A/C NOT FOR ALL | ------------------------------------------------------------------------------- |
| FIN I FUNCTIONAL DESIGNATION I PANELIZONEIACCESS I ATA |
| I I I I DOOR I REF. |
| ------------------------------------------------------------------------------- |
| - LP COMPRESSOR MODULE 435 437AL 72-31-00 |
| - LP COMPRESSOR BLADES AND FILLERS 435 72-31-11 |
| - PANEL-REAR,FAN CASE 445 451AL 72-32-87 |
| - OUTLET GUIDE VANES-LP COMPRESSOR 435 451AL 72-32-88 |
| - ACOUSTIC LINING 435 72-32-89 |
| - INLET CONE 435 72-38-11 |
| - ACCESSORY DRIVES (EXTERNAL GEARBOX) 435 437AL 72-60-00 |
3. Engine Modules
The engine modules are:
The fan module, the intercase module, the HPC, the diffuser/combustor module, the HPT, the LPT and the accessory drive gearbox. A detailed description of the components of each module is given in the corresponding sections of this document.
The description of each module is as follows:
The engine modules are:
The fan module, the intercase module, the HPC, the diffuser/combustor module, the HPT, the LPT and the accessory drive gearbox. A detailed description of the components of each module is given in the corresponding sections of this document.
The description of each module is as follows:
A. Fan Module
It consists of a single stage, wide-chord, shroudless fan and hub.
It consists of a single stage, wide-chord, shroudless fan and hub.
B. Intercase Module
It consists of the fan containment case, fan Exit Guide Vanes (EGV), intermediate case, booster, low spool stubshaft, the accessory gearbox towershaft drive assembly, high spool stubshaft and the station 2.5 bleed valve (BSBV). The booster consists of inlet stators, rotor assembly, and outlet stators. The No. 1, 2 and 3 (front) bearing compartment is built into the module and contains the support bearings for the low spool and high spool stubshafts.
In conjunction with the inner fan section, the booster increases the pressure at the entrance to the HPC and provides an even pressure profile to improve efficiency. The station 2.5 bleed is used for engine handling by controlling airflow to the high compressor entrance.
It consists of the fan containment case, fan Exit Guide Vanes (EGV), intermediate case, booster, low spool stubshaft, the accessory gearbox towershaft drive assembly, high spool stubshaft and the station 2.5 bleed valve (BSBV). The booster consists of inlet stators, rotor assembly, and outlet stators. The No. 1, 2 and 3 (front) bearing compartment is built into the module and contains the support bearings for the low spool and high spool stubshafts.
In conjunction with the inner fan section, the booster increases the pressure at the entrance to the HPC and provides an even pressure profile to improve efficiency. The station 2.5 bleed is used for engine handling by controlling airflow to the high compressor entrance.
C. High Pressure Compressor
The HPC is a ten stage, axial flow module. It is comprised of the drum rotor assembly, the front casing which houses the variable geometry vanes and the rear casing which contains the fixed geometry stators and forms the bleed manifolds.
The HPC is a ten stage, axial flow module. It is comprised of the drum rotor assembly, the front casing which houses the variable geometry vanes and the rear casing which contains the fixed geometry stators and forms the bleed manifolds.
D. Diffuser/Combustor Module
The combustion section consists primarily of the diffuser case, combustor, fuel injector and ignitors. The high compressor exit guide vanes and the No. 4 bearing compartment are also part of the module.
The main features of the module include a close-coupled prediffuser and combustor that provide low velocity shroud air to feed the combustor liners and to minimize performance losses.
The combustion section consists primarily of the diffuser case, combustor, fuel injector and ignitors. The high compressor exit guide vanes and the No. 4 bearing compartment are also part of the module.
The main features of the module include a close-coupled prediffuser and combustor that provide low velocity shroud air to feed the combustor liners and to minimize performance losses.
E. High Pressure Turbine
The HPT is a two stage turbine and drives the HPC and the accessory gearbox.
The HPT is a two stage turbine and drives the HPC and the accessory gearbox.
F. Low Pressure Turbine
The LPT is a five stage module. The elliptical leading edge airfoils improve the aerodynamic efficiency. Module efficiency is further enhanced by incorporation of rim seals and clustered vanes which results in reduced losses due to leakage. Active clearance control is used to control seal clearances and to provide structural cooling.
The LPT is a five stage module. The elliptical leading edge airfoils improve the aerodynamic efficiency. Module efficiency is further enhanced by incorporation of rim seals and clustered vanes which results in reduced losses due to leakage. Active clearance control is used to control seal clearances and to provide structural cooling.
G. Accessory Drive Gearbox
The accessory drive gearbox provides shaft horse power to drive engine and aircraft accessories. These include fuel, oil and hydraulic pressure pumps and electrical power generators for the EEC and for the aircraft. The gearbox also includes provision for a starter which is used to drive the N2 shaft for engine starting.
The accessory drive gearbox provides shaft horse power to drive engine and aircraft accessories. These include fuel, oil and hydraulic pressure pumps and electrical power generators for the EEC and for the aircraft. The gearbox also includes provision for a starter which is used to drive the N2 shaft for engine starting.