Editing Combustor (section)

===Can-annular===
[[File:CanAnnularCombustor.svg|thumb|right|Cannular combustor for a gas turbine engine, viewing axis on, through the exhaust]]

The next type of combustor is the "can-annular"<ref>Federal Aviation Administration, FAA-H-8083-32A, Aviation Maintenance Technician Handbook - Powerplant Volume 1, p.1-44</ref> combustor. Like the can-type combustor, can-annular combustors have discrete combustion zones contained in separate liners with their own fuel injectors. Unlike the can combustor, all the combustion zones share a common ring (annulus) casing. Each combustion zone no longer has to serve as a pressure vessel.<ref>Mattingly, Heiser, and Pratt, pp. 377–8.</ref> The combustion zones can also "communicate" with each other via liner holes or connecting tubes that allow some air to flow circumferentially. The exit flow from the can-annular combustor generally has a more uniform temperature profile, which is better for the turbine section. It also eliminates the need for each chamber to have its own igniter. Once the fire is lit in one or two cans, it can easily spread to and ignite the others. This type of combustor is  also lighter than the can type, and has a lower pressure drop (on the order of 6%). However, a can-annular combustor can be more difficult to maintain than a can combustor.<ref>Flack, pp. 442–4.</ref> Examples of gas turbine engines utilizing a can-annular combustor include the [[General Electric J79]] [[turbojet]] and the [[Pratt & Whitney TF30]] and [[Rolls-Royce RB.183 Tay|Rolls-Royce Tay]] [[turbofans]].<ref>Henderson and Blazowski, pp. 106–7.</ref>