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JET ENGINE THEORY AND DESIGN

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JET ENGINE THEORY AND DESIGN ( jet-engine-theory-and-design )

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The three basic types of combustion chambers are as follows:  The multiple chamber, or can.  The annular, or basket.  The can-annular. Can Type The can-type combustion chamber is typical of the type used on axial-flow engines. Can-type combustion chambers are arranged radially around the axis of the engine. The amount of chambers will vary in number. In the past (or development years) as few as 2 and as many as 16 chambers have been used. The present trend shows the use of about 8 or 10 combustion chambers. Figure 1-26 shows the liner of a can-type combustion chamber. These chambers are numbered in a clockwise direction. As you face the rear of the engine and look forward, the number 1 chamber is at the top. Some provision is made in the combustion chamber case or in the compressor air outlet elbow for the installation of a fuel nozzle. The fuel nozzle delivers the fuel into the liner in a finely atomized spray. The finer the spray, the more rapid and efficient the burning process becomes. The two types of fuel nozzles being used in the various types of combustion chambers are the simplex nozzle and the duplex nozzle. The fuel nozzles are constructed so they can be installed in various ways. The two methods used most frequently are external mounting and internal mounting. In external mounting, a mounting pad is provided for attachment of the nozzle to the case or the inlet air elbow, with the nozzle tip projecting into the chamber liner, usually near the dome. When internal mounting at the liner dome, the chamber cover is removed for replacement or maintenance of the nozzle. The simplex nozzle (Figure 1- 27), with its single orifice, does not provide a satisfactory spray over a wide range of operating conditions. Therefore, its use on current models of jet engines Figure 1-26 — Can-type combustion liner. Figure 1-27 — simplex/duplex spray nozzles. 1-18

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