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As we read previously, igniter plugs function during start up and are cut out of the circuit as soon as combustion is self supporting (the turbine has developed design speed and is driving the compressor on its own). On engine shutdown, or, if start failure occurs, the combustion chamber drain pressure-actuated valve, automatically drains any raw fuel from the combustion chamber. The material suitable for fabricating the combustion chamber liner is typically welded high-nickel steel. The hottest zone is about the first upstream third of its length (flame zone). The most severe operating periods in combustion chambers are during engine idle (reduced air) and maximum rpm (power) operation. Sustained operation is generally unnecessary. “Base load” with a ground based gas turbine is generally a power setting lower than this value. With aircraft engine operation, maximum rpm generally corresponds to maximum (take off) thrust. The annular combustion chamber can enhance a geometrically compact design. Instead of individual combustion chamber cans, compressed air is introduced into an annular space formed by a chamber liner that may be situated in some designs, around the turbine assembly. Annular space left between the outer liner wall and the combustion chamber housing conducts the flow of compressor secondary cooling air. Primary air is mixed with the fuel for combustion. Secondary (cooling) air reduces the temperature of the hot gases seen by the turbine first stage inlet nozzle guide vanes (IGVs). An annular combustion chamber provides a larger combustion volume per unit of exposed metal area and therefore of metal weight. The can combustion chamber design has individual combustion chambers. Air from the compressor enters each individual chamber through a transition section. Each individual can has two cylindrical tubes, concentric in most locations, the combustion chamber liner and the outer combustion chamber. Combustion occurs within the inner liner. Louvers and holes control airflow into the combustion area. Continuous airflow helps prevent carbon from forming on the inside of the liner. Carbon deposits can cause hot spots or block cooling air passages, which then shortens burner life. Ignition occurs during the start cycle. The igniter plug(s) is (are) located in the combustion liner adjacent to the start fuel nozzle. Two is a typical number. The flame lights off in the can closest the igniter and cross tubes rapidly conduct the flame to the other combustion cans. Some engines use a single can combustor. In the case of the illustration below, because of the size of the single can, the design is referred to as a “silo” burner. This design can be vulnerable to one or more of the heat shield tiles that line the inside of the silo, breaking loose and potentially proceeding downstream into the turbine’s gas path. Fig. 30. GE 9H partial combustion module during manufacture (Source: GE Power Systems) 24PDF Image | GAS TURBINES IN SIMPLE CYCLE COMBINED CYCLE APPLICATIONS
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