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The advantages of the axial-flow compressor are as follows: High peak efficiencies. Low frontal area for given airflow. Straight-through flow, allowing high ram efficiency. Increased pressure rise by increasing the number of stages, with negligible losses. The disadvantages of the axial-flow compressor are as follows: Good efficiencies are possible over narrow rotational-speed range only. Difficulty of manufacture and high cost. High starting-power requirements. Because of its similarity to compressors, the fan of a turbofan engine should be mentioned now. The fan accelerates a large mass of air rearward. It requires relatively low drive power, and has a pressure ratio of 2 to 1 or less. It can be thought of as a pre-compressor, as air enters the compressor inlet at a pressure about 1.5-2.0 to 1 atmosphere. COMBUSTION SECTION The combustion section provides the means for and houses the combustion process. Its function is to raise the temperature of the air passing through the engine. This process releases energy contained in the air and fuel. The major part of this energy drives the compressor. The remaining energy creates the reaction (or propulsion) and passes out the rear of the engine in the form of a high-velocity jet. The primary considerations in burning the fuel-air mixture include: Providing the means for proper mixing of the fuel and air to assure good combustion. Burning this mixture efficiently. Cooling the hot combustion products to a temperature that the turbine blades can withstand under operating conditions. Directing the hot gases to the turbine section. The location of the combustion section is directly between the compressor and the turbine sections. The combustion chambers are arranged coaxially with the compressor and turbines. The chambers must be in a through-flow position to function efficiently. About one-fourth of the air entering the combustion chamber area mixes with the fuel for combustion. This is primary air. The remaining air (secondary air) serves as flame control. Keeping the temperature of the heated gases down to a level at which the liners, turbine nozzles, or blades will not burn. These basic requirements apply to all combustion sections. Another general requirement of combustion chambers is air pollution emission reduction. Pollution emissions are particles of matter, such as smoke, carbon monoxide, partially burned hydrocarbons, and nitric oxides. In general, exhaust smoke becomes a problem when combustors operate at pressure greater than 10 atmospheres and when the fuel-air ratio in the primary zone of the combustor is rich. For example, in the idle range of operation, both smoke particles and partially burned hydrocarbons emit. During the combustion process, emission levels of nitric oxide increase with temperature increases to about 2,600 °F. At this temperature, these emission levels begin to taper off. There is research being conducted to correct problems, but many new factors may influence the solution of the pollution problem. All combustion chambers contain the same basic elements: a casing, a perforated inner liner, a fuel injection system, some means for initial ignition, and a fuel drainage system to drain off unburned fuel after engine shutdown. 1-17PDF Image | JET ENGINE THEORY AND DESIGN
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