An engine that uses an annular combustor is the CFM International CFM56. This auxiliary chamber is smaller in size than the main combustion chamber and is called the pre-combustion chamber. All combustion chambers contain the same basic elements: Fuel drainage system to drain off unburned fuel after engine shutdown. Most modern gas turbine engines (particularly for aircraft applications) do not use can combustors, as they often weigh more than alternatives. Annular combustors do away with the separate combustion zones and simply have a continuous liner and casing in a ring (the annulus). [Figure 1] Each of the can-type combustion chambers consists of an outer case or housing, within which there is a perforated stainless steel (highly heat resistant) combustion chamber liner or inner liner. Once the fire is lit in one or two cans, it can easily spread to and ignite the others. Each combustion zone no longer has to serve as a pressure vessel. Most modern engines use annular combustors; likewise, most combustor research and development focuses on improving this type. The primary function of the combustion section is, of course, to burn the fuel/air mixture, thereby adding heat energy to the air. These types are: The can-type combustion chamber is typical of the type used on turboshaft and APUs. There are two combustion chambers one is auxiliary combustion chamber and the other is the main combustion chamber. The exit flow from the cannular combustor generally has a more uniform temperature profile, which is better for the turbine section. Older engines with several combustion cans had each can with interconnector (flame propagation) tube, which was a necessary part of the can-type combustion chambers. The primary air from the compressor is guided into each individual can, where it is decelerated, mixed with fuel, and then ignited. The remaining energy passes through the remaining turbine stages that absorb more of the energy to drive the fan, output shaft, or propeller. • These are: Can, Cannular and Annular. [Figure 1] The air entering the combustion chamber is divided by the proper holes, louvers, and slots into two main streams—primary and secondary air. The annular combustion chamber is illustrated in Figure 7. The major part of this energy is required at the turbine or turbine stages to drive the compressor. The air flow direction is indicated by the arrows. Each "can" has its own fuel injector, igniter, liner, and casing. To do this efficiently, the combustion chamber must: Provide the means for proper mixing of the fuel and air to assure good combustion, Cool the hot combustion products to a temperature that the turbine inlet guide vanes/blades can withstand under operating conditions, and. The vigorous mechanical mixing of the fuel vapor with the primary air is necessary, since mixing by diffusion alone is too slow. The spark igniter plugs of the annular combustion chamber are the same basic type used in the can-type combustion chambers, although construction details may vary. These chambers are spaced around the shaft connecting the compressor and turbine, each chamber having its own fuel jet fed from a common supply line. There are usually two igniters mounted on the boss provided on each of the chamber housings. The flame tubes vary in construction details from one engine to another, although the basic components are almost identical. There are three main types of combustors, and all three designs are found in modern gas turbines: The burner at the left is an annular combustor with the liner sitting inside the outer casing which has been peeled open in the drawing. In an internal combustion engine, the pressure caused by the burning air/fuel mixture applies direct force to part of the engine (e.g. 4. Like the can type combustor, can annular combustors have discrete combustion zones contained in separate liners with their own fuel injectors. Can type combustors were most widely used in early gas turbine engines, owing to their ease of design and testing (one can test a single can, rather than have to test the whole system). Create your own unique website with customizable templates. [Figure 3] The spark igniters previously mentioned are normally two in number, and are located in two of the can-type combustion chambers. The combustion zones can also "communicate" with each other via liner holes or connecting tubes that allow some air to flow circumferentially.

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