DOC AIRBUS | AMM A320FCOMBUSTION CHAMBER ASSEMBLY - DESCRIPTION AND OPERATION
** ON A/C NOT FOR ALL
1. General
The combustion case contains the combustion chamber, which is a short, annular structure. The combustion chamber consists of outer and inner cowls, 20 primary swirl nozzles, dome, and outer and inner liners. The liners and cowls are bolted to the dome.
The function of the combustion chamber is to supply a uniform combustion pattern for low thermal stress.
The staged burning valve, controlled by FADEC, adapts the function of the combustion chamber to the engine requirements by the use of either 10 or 20 open fuel nozzles.
** ON A/C NOT FOR ALL The combustion case contains the combustion chamber, which is a short, annular structure. The combustion chamber consists of outer and inner cowls, 20 primary swirl nozzles, dome, and outer and inner liners. The liners and cowls are bolted to the dome.
Combustion ChamberThe function of the combustion chamber is to supply a uniform combustion pattern for low thermal stress.
The staged burning valve, controlled by FADEC, adapts the function of the combustion chamber to the engine requirements by the use of either 10 or 20 open fuel nozzles.
2. Description
A. Dome
The dome consists of both cast and machined components. Twenty primary swirl nozzles and 20 secondary swirl nozzles with venturies and sleeves are used to provide mixing of air and fuel. The entire surface of the dome is cooled by a film of cooling air.
The dome consists of both cast and machined components. Twenty primary swirl nozzles and 20 secondary swirl nozzles with venturies and sleeves are used to provide mixing of air and fuel. The entire surface of the dome is cooled by a film of cooling air.
B. Cowls
The inner and outer cowls are designed to provide uniform and stable airflow profiles to the combustion chamber.
The inner and outer cowls are designed to provide uniform and stable airflow profiles to the combustion chamber.
C. Liners
The outer and inner liners are of an integral design with panel overhangs which contain closely spaced cooling holes that provide film cooling.
Dilution holes are employed in the liners to provide additional mixing and cooling air which lowers the gas temperature at the turbine inlet. The outer liner contains 2 ferrules for the spark igniters.
The outer and inner liners are of an integral design with panel overhangs which contain closely spaced cooling holes that provide film cooling.
Dilution holes are employed in the liners to provide additional mixing and cooling air which lowers the gas temperature at the turbine inlet. The outer liner contains 2 ferrules for the spark igniters.