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23 Fig. 29. Annual Combustion Chambers Source: Courtesy of Butterworth Heinemann, from “Process Plant Machinery” 2nd Edition, Bloch, H. and Soares, C., 1998 Some variations on these basic designs occur in specialized applications. Again, one example is US Army helicopters that use the annular reverse-row type. The combustor module contains the combustion chambers, igniter plugs, and fuel nozzles. The combustor burns a fuel-air mixture and delivers the products of combustion to the turbine at temperatures within design range. Fuel is injected at the upstream end of the burner in a highly atomized spray. Fuel nozzles may be simplex type (delivering gaseous fuel or liquid fuel) or they may be designed to be dual fuel (delivering gas or liquid at different times in the operation). Some gas turbines are “bi-fuel”. They may burn a mixture of gas and liquid fuel. 1.1 Simple and Combined Cycles Combustion air, with the help of swirler vanes, flows in around the fuel nozzle and mixes with the fuel. This air is called primary air and represents approximately 25 percent of total air ingested by the engine. The fuel-air mixture by weight is roughly 15 parts of air to 1 part of fuel. The remaining 75 percent of the air is used to form an air blanket around the burning gases and to lower the temperature. Flame temperatures in excess of 3600° F (roughly 200 degrees C) are not uncommon in high performance aircraft engines. Cooling air drops this temperature to a value that the turbine inlet guide vanes can withstand. The air used for burning fuel is “primary” air. Cooling air is “secondary” air and is controlled and directed by holes and louvers in the combustion chamber liner. Certain aircraft engines are termed high bypass ratio fan engines. With this design, the gas turbine has an inlet fan upstream of the low pressure compressor (LPC). That fan’s diameter is far larger than that of the LPC. Much of the air ingested by the fan is directed through an annular sleeve type casing that fits around the compressor. This bypass air provides still more cooling but also helps with other gas turbine performance characteristics like power developed, total mass flow and FOD ingestion capabilities.PDF Image | GAS TURBINES IN SIMPLE CYCLE COMBINED CYCLE APPLICATIONS
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