DOC AIRBUS | AMM A320FCOMBUSTION SECTION - DESCRIPTION AND OPERATION
** ON A/C NOT FOR ALL
1. General
The combustion section consists of the combustion case assembly (Ref. AMM D/O 72-41-00-00) and the combustion chamber assembly (Ref. AMM D/O 72-42-00-00). The combustion section mixes fuel and High Pressure Compressor (HPC) air for efficient and uniform combustion.
** ON A/C NOT FOR ALL The combustion section consists of the combustion case assembly (Ref. AMM D/O 72-41-00-00) and the combustion chamber assembly (Ref. AMM D/O 72-42-00-00). The combustion section mixes fuel and High Pressure Compressor (HPC) air for efficient and uniform combustion.
Combustion Section - General2. System Description
A. Combustion Section
(1) The LEAP-1A combustion section consists of:
(a) The Combustion Case Assembly
The combustion case consists of the combustor diffuser nozzle case, Outlet Guide Vanes (OGVs), the diffuser and the abradable portion of the Compressor Discharge Pressure (CDP) stator seal.
The combustion case consists of the combustor diffuser nozzle case, Outlet Guide Vanes (OGVs), the diffuser and the abradable portion of the Compressor Discharge Pressure (CDP) stator seal.
(b) The Combustion Chamber Assembly
The combustor diffuser nozzle case is a life limited part that supports the combustion chamber assembly inner and outer liners and provides a mounting location for the nineteen fuel nozzles and the two igniters. The combustor diffuser nozzle case provides the structural load path between the rear HPC stator case and High Pressure Turbine (HPT) stator case.
The combustor diffuser nozzle case is a life limited part that supports the combustion chamber assembly inner and outer liners and provides a mounting location for the nineteen fuel nozzles and the two igniters. The combustor diffuser nozzle case provides the structural load path between the rear HPC stator case and High Pressure Turbine (HPT) stator case.
(c) OGV/Diffuser
OGVs are used to direct the air axially, from stage 10 of the HPC to feed the combustion chamber with the correct airflow angle for more efficient use in the combustion process.
OGVs are used to direct the air axially, from stage 10 of the HPC to feed the combustion chamber with the correct airflow angle for more efficient use in the combustion process.
(d) The Diffuser
The diffuser is used to increase the static pressure of the air by reducing the velocity to feed the combustion chamber with the correct airflow for more efficient use in the combustion process. The diffuser provides structural support for the OGV and static abradable CDP stator seal, as well as the HPT stage 1 nozzle support.
The diffuser is used to increase the static pressure of the air by reducing the velocity to feed the combustion chamber with the correct airflow for more efficient use in the combustion process. The diffuser provides structural support for the OGV and static abradable CDP stator seal, as well as the HPT stage 1 nozzle support.
(e) CDP Stator Seal
The HPC discharge pressure rotating air seal bolted to the rear arm of the HPC stage 6-10 spool. The CDP rotating air seal interfaces with the abradable CDP stator seal to ensure that the HPC stage 10 pressurized air flows through the diffuser.
The HPC discharge pressure rotating air seal bolted to the rear arm of the HPC stage 6-10 spool. The CDP rotating air seal interfaces with the abradable CDP stator seal to ensure that the HPC stage 10 pressurized air flows through the diffuser.
(f) Combustion Chamber Assembly (Ref. AMM D/O 72-42-00-00)
The combustion chamber assembly consists of nineteen twin annular premixing swirler fuel nozzles, the combustion chamber dome, the inner liner, and the outer liner, the radial mixer and the inner and outer baffle. The combustion chamber assembly provides containment of high pressure and temperature air.
The combustion chamber assembly consists of nineteen twin annular premixing swirler fuel nozzles, the combustion chamber dome, the inner liner, and the outer liner, the radial mixer and the inner and outer baffle. The combustion chamber assembly provides containment of high pressure and temperature air.
(g) Fuel Nozzles
The twin annular premixing swirler fuel nozzles introduce fuel to the combustion chamber and the radial mixers that mix the fuel and air required for combustion. The twin annular premixing swirler combustion chamber assembly is designed to reduce NOX emissions while providing a shorter combustion chamber length as compared to non-twin annular premixing swirler combustion chambers.
The twin annular premixing swirler fuel nozzles introduce fuel to the combustion chamber and the radial mixers that mix the fuel and air required for combustion. The twin annular premixing swirler combustion chamber assembly is designed to reduce NOX emissions while providing a shorter combustion chamber length as compared to non-twin annular premixing swirler combustion chambers.
NOTE: NOX is an abbreviation commonly used to include the gases NO (Nitric Oxide) and NO2 (nitrogen dioxide) that are formed as a result of burning hydro-carbon fuels.
The twin annular premixing swirler fuel nozzles are dual flow with a primary and main circuit to better optimize the combustion process across the operating envelope to improve efficiency and lower emissions. The twin annular premixing swirler fuel nozzles are mounted through the combustor diffuser nozzle case and the combustion chamber dome and into the combustion chamber. (h) Combustor Chamber Dome
The combustion chamber dome is the forward wall of the combustion chamber. The radial mixers, inner and outer liners are attached to the combustion chamber dome. The combustion chamber dome directs hot combustion gases aft.
The combustion chamber dome is the forward wall of the combustion chamber. The radial mixers, inner and outer liners are attached to the combustion chamber dome. The combustion chamber dome directs hot combustion gases aft.
(i) Radial Mixer
Each twin annular premixing swirler fuel nozzle is surrounded by a radial mixer mounted on the combustion chamber dome. The radial mixer takes diffuser-air and spins the air prior to being mixed with fuel.
Each twin annular premixing swirler fuel nozzle is surrounded by a radial mixer mounted on the combustion chamber dome. The radial mixer takes diffuser-air and spins the air prior to being mixed with fuel.
(j) Inner Liner
The inner liner forms the inboard portion of the combustion chamber assembly. The inner liner has cooling holes and is covered by a thermal barrier coating to protect it from the energy generated by the combustion process. The inner liner directs hot gases into the HPT stage 1 nozzles.
The inner liner forms the inboard portion of the combustion chamber assembly. The inner liner has cooling holes and is covered by a thermal barrier coating to protect it from the energy generated by the combustion process. The inner liner directs hot gases into the HPT stage 1 nozzles.
(k) Outer Liner
The outer liner forms the outboard portion of the combustion chamber assembly. The outer liner has cooling holes and is covered by a thermal barrier coating to protect it from the energy generated by the combustion process. The outer liner directs hot gases into the HPT stage 1 nozzles. The outer liner also provides local penetrations for the igniters and the borescope ports.
The outer liner forms the outboard portion of the combustion chamber assembly. The outer liner has cooling holes and is covered by a thermal barrier coating to protect it from the energy generated by the combustion process. The outer liner directs hot gases into the HPT stage 1 nozzles. The outer liner also provides local penetrations for the igniters and the borescope ports.
(l) Inner Baffle
The inner liner of the combustion chamber assembly has an inner baffle with cooling holes for improved cooling effectiveness of the inner liner.
The inner liner of the combustion chamber assembly has an inner baffle with cooling holes for improved cooling effectiveness of the inner liner.
(m) Outer Baffle
The outer liner of the combustion chamber assembly has an outer baffle with cooling holes for improved cooling effectiveness of the outer liner.
The outer liner of the combustion chamber assembly has an outer baffle with cooling holes for improved cooling effectiveness of the outer liner.