3.2.3.1 Combustion System Description
The combustion system is of the reverse-flow type with the 18 combustion chambers arranged around the periphery of the compressor discharge casing as shown on Figure (3.15). Combustion chambers are numbered counterclockwise when viewed looking downstream and starting from the top left of the machine.
This system also includes the fuel nozzles, a spark plug ignition system, flame detectors and cross fire tubes as shown in figure(3.1
Hot gases generated from burning fuel in the combustion chambers flows through the impingement cooled transition pieces to the turbine as shown in figure (3.17).
High pressure air from the compressor discharge is directed around the transition pieces. Some of the air enters the holes in the impingement sleeve to cool the transition pieces and flows into the flow sleeve. The rest enters the annulus between the flow sleeve and the combustion liner through holes in the downstream end of the flow sleeve as shown in figure (3.18). This air enters the combustion zone through the cap assembly for proper fuel combustion. Fuel is supplied to each combustion chamber through five nozzles designed to disperse and mix the fuel with the proper amount of combustion air.
3.2.3.2 Combustion System Options
Dual fuel combustion system is a single stage, dual mode combustor capable of operation on both gaseous and liquid fuel. Gas Fuel only-On gas the combustor operates in a diffusion mode at low loads (<50% load) and a pre-mixed mode at high loads (>50% load). While the combustor is capable of operating in the diffusion mode across the load range. Diluents injection would be required for NOx abatement. Liquid fuel only- On oil operation, this combustor is in the diffusion mode across the entire load range, with diluents injection used for Nox abatement.
The combustion system is of the reverse-flow type with the 18 combustion chambers arranged around the periphery of the compressor discharge casing as shown on Figure (3.15). Combustion chambers are numbered counterclockwise when viewed looking downstream and starting from the top left of the machine.
This system also includes the fuel nozzles, a spark plug ignition system, flame detectors and cross fire tubes as shown in figure(3.1
Hot gases generated from burning fuel in the combustion chambers flows through the impingement cooled transition pieces to the turbine as shown in figure (3.17).
High pressure air from the compressor discharge is directed around the transition pieces. Some of the air enters the holes in the impingement sleeve to cool the transition pieces and flows into the flow sleeve. The rest enters the annulus between the flow sleeve and the combustion liner through holes in the downstream end of the flow sleeve as shown in figure (3.18). This air enters the combustion zone through the cap assembly for proper fuel combustion. Fuel is supplied to each combustion chamber through five nozzles designed to disperse and mix the fuel with the proper amount of combustion air.
3.2.3.2 Combustion System Options
Dual fuel combustion system is a single stage, dual mode combustor capable of operation on both gaseous and liquid fuel. Gas Fuel only-On gas the combustor operates in a diffusion mode at low loads (<50% load) and a pre-mixed mode at high loads (>50% load). While the combustor is capable of operating in the diffusion mode across the load range. Diluents injection would be required for NOx abatement. Liquid fuel only- On oil operation, this combustor is in the diffusion mode across the entire load range, with diluents injection used for Nox abatement.
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