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Can-Annular Type The can-annular type combustion chamber is a development by Pratt and Whitney for use in their J57 axial-flow turbojet engine. Since this engine features the split-spool compressor, it requires combustion chambers capable of meeting the stringent requirements of maximum strength, limited length, and high overall efficiency. These attributes are necessary because of the high air pressures and velocities present in a split-spool compressor, along with the shaft length limitations. The split- spool compressor requires two concentric shafts joining the turbine stages to their respective compressors. The front compressor, joined to the rear turbine stages, requires the longest shaft. This shaft is inside the other. A limitation of diameter is imposed, so that the distance between the front compressor and the rear turbine must be limited if critical shaft lengths are to be avoided. (High torque is present if there is a long shaft of small diameter.) Since the compressor and turbine are not susceptible to shortening, this shaft length limitation is addressed by developing a new type of burner, a design that would give the desired performance in much less relative linear distance. The can-annular combustion chambers are arranged radially around the axis of the engine; the axis in this instance being the rotor shaft housing. The combustion chambers are enclosed by a removable steel shroud, which covers the entire burner section. This feature makes the burners readily available for any required maintenance. The burners are interconnected by projecting flame tubes, which help the engine-starting process in the can-type combustion chamber. These flame tubes perform a function identical with those previously discussed, the only difference being in construction details. Figure 1-30 also reveals that each of the combustion chambers contains a central bullet-shaped perforated liner. The size and shape of the perforations are predetermined to admit the correct quantity of air at the velocity and angle required to control the flame pattern. Cutouts are provided in two of the bottom chambers for installation of the spark igniters. Figure 1-30 shows how the forward face of the chambers presents apertures that align with the six fuel nozzles of the corresponding fuel nozzle cluster. As in the can-type combustion chamber, these nozzles are the dual-orifice (duplex) type that requires the use of a flow-divider (pressurizing valve). Pre-swirl vanes are located around each of the nozzles for imparting a swirling motion to the fuel spray. This results in better atomization of the fuel, thus better burning and efficiency. The swirl vanes perform two important functions imperative to proper flame propagation: High flame speed, providing better mixing of air and fuel, ensuring spontaneous burning. Swirling, preventing the flame from moving rapidly rearward. The swirl vanes greatly aid flame propagation, since a high degree of turbulence in the early combustion and cooling stages is desirable. The vigorous mechanical mixing of the fuel vapor with the primary air is necessary, since mixing by diffusion alone is too slow. This same mechanical mixing is also established by other means, such as placing coarse screens in the diffuser outlet, as is the case in most axial-flow engines. The can-annular combustion chambers also must have the required fuel drain valves, located in two or more of the bottom chambers, thereby assuring proper drainage and Figure 1-31 — Airflow through a can-annular chamber. 1-22PDF Image | JET ENGINE THEORY AND DESIGN
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