DOC AIRBUS | AMM A320FCOMBUSTION CASE ASSEMBLY - DESCRIPTION AND OPERATION
** ON A/C NOT FOR ALL
1. General
The combustion case is a fabricated structural weldment located between the high pressure compressor (HPC) and the low pressure turbine (LPT). It provides the structural interface, transmits the engine axial load, and provides gas flow path between the compressor and LPT. The case incorporates the compressor outlet guide vanes (OGV) and a diffuser for the reduction of combustion chamber sensitivity to the compressor air velocity profile.
** ON A/C NOT FOR ALL The combustion case is a fabricated structural weldment located between the high pressure compressor (HPC) and the low pressure turbine (LPT). It provides the structural interface, transmits the engine axial load, and provides gas flow path between the compressor and LPT. The case incorporates the compressor outlet guide vanes (OGV) and a diffuser for the reduction of combustion chamber sensitivity to the compressor air velocity profile.
Combustion Case2. Description
A. Components
The combustion case encloses the combustion chamber and high pressure turbine (HPT) components. The combustion chamber, compressor rear stationary (CDP) seal, HPT nozzle assembly, and HPT shroud/stage 1 LPT nozzle assembly are mounted in and structurally supported by the combustion case. The case mounts and positions the 20 fuel nozzles, 2 igniters, and fuel manifold.
The fuel manifold system is composed of a fuel supply manifold (Y tube), 2 fuel manifolds halves, 3-piece drain manifold, and overboard drain tube.
The combustion case encloses the combustion chamber and high pressure turbine (HPT) components. The combustion chamber, compressor rear stationary (CDP) seal, HPT nozzle assembly, and HPT shroud/stage 1 LPT nozzle assembly are mounted in and structurally supported by the combustion case. The case mounts and positions the 20 fuel nozzles, 2 igniters, and fuel manifold.
The fuel manifold system is composed of a fuel supply manifold (Y tube), 2 fuel manifolds halves, 3-piece drain manifold, and overboard drain tube.
B. Ports
There are 6 borescope ports ; 4 for inspection of the combustion chamber and HPT nozzles and 2 for inspection of the HPT blades and shrouds and the stage 1 LPT blades. The case has 4 ports for extraction of compressor discharge air for customer use, 4 ports for introduction of stage 5 compressor air for low pressure cooling and 3 ports for HPT shroud cooling air (one for source air and 2 for introduction of air to the shrouds). There is also one port for the following : start bleed dump, P3 sensor, T3 sensor, and CCCP air. There are 2 ports for the spark igniters and 2 ports for turbine clearance control thermocouples.
There are 6 borescope ports ; 4 for inspection of the combustion chamber and HPT nozzles and 2 for inspection of the HPT blades and shrouds and the stage 1 LPT blades. The case has 4 ports for extraction of compressor discharge air for customer use, 4 ports for introduction of stage 5 compressor air for low pressure cooling and 3 ports for HPT shroud cooling air (one for source air and 2 for introduction of air to the shrouds). There is also one port for the following : start bleed dump, P3 sensor, T3 sensor, and CCCP air. There are 2 ports for the spark igniters and 2 ports for turbine clearance control thermocouples.