Editing Combustor (section)

===Can===
Can combustors are self-contained cylindrical combustion chambers. Each "can" has its own fuel injector, igniter, liner, and casing.<ref name="nasa">Benson, Tom. [https://www.grc.nasa.gov/WWW/K-12/airplane/burner.html Combustor-Burner]. NASA Glenn Research Center. Last Updated 11 Jul 2008. Accessed 6 Jan 2010.</ref> The primary air from the compressor is guided into each individual can, where it is decelerated, mixed with fuel, and then ignited. The secondary air also comes from the compressor, where it is fed outside of the liner (inside of which is where the combustion is taking place). The secondary air is then fed, usually through slits in the liner, into the combustion zone to cool the liner via thin film cooling.<ref>Flack, p. 442.</ref>

In most applications, multiple cans are arranged around the central axis of the engine, and their shared exhaust is fed to the {{not a typo|turbine(s)}}. 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). Can-type combustors are easy to maintain, as only a single can needs to be removed, rather than the whole combustion section. Most modern gas turbine engines (particularly for aircraft applications) do not use can combustors, as they often weigh more than alternatives. Additionally, the pressure drop across the can is generally higher than other combustors (on the order of 7%). Most modern engines that use can combustors are [[turboshafts]] featuring [[centrifugal compressor]]s.<ref>Flack, pp. 442–3.</ref><ref>Henderson and Blazowski, p. 106.</ref><ref>https://armyaviation.tpub.com/AL0993/Figure-1-20-Can-Annular-Combustion-Chamber-134.htm</ref><ref>https://www.aircav.com/gencombu.html</ref>