Editing Combustor (section)

==Ramjets==
{{Main|Ramjet}}
[[Ramjet]] engines differ in many ways from traditional gas turbine engines, but most of the same principles hold. One major difference is the lack of rotating machinery (a turbine) after the combustor. The combustor exhaust is directly fed to a nozzle. This allows ramjet combustors to burn at a higher temperature. Another difference is that many ramjet combustors do not use liners like gas turbine combustors do. Furthermore, some ramjet combustors are ''dump combustors'' rather than a more conventional type. Dump combustors inject fuel and rely on recirculation generated by a large change in area in the combustor (rather than swirlers in many gas turbine combustors).<ref name="fh">Stull, F. D. and Craig, R. R. (1975). Investigation of Dump Combustors with Flameholders. ''13th AIAA Aerospace Sciences Meeting''. Pasadena, CA. 20–22 January 1975. AIAA 75-165</ref> That said, many ramjet combustors are also similar to traditional gas turbine combustors, such as the combustor in the ramjet used by the [[RIM-8 Talos]] missile, which used a can-type combustor.<ref name="hist">{{cite journal |author1=Waltrup, P.J. |author2=White M.E. |author3=Zarlingo F |author4=Gravlin E. S. |title=History of U.S. Navy Ramjet, Scramjet, and Mixed-Cycle Propulsion Development |journal=Journal of Propulsion and Power |volume=18 |number=1 |date=January–February 2002 |pages=14–27 |doi=10.2514/2.5928 |url=https://arc.aiaa.org/doi/abs/10.2514/2.5928 |url-status=live |archive-url=https://web.archive.org/web/20070413051619/http://pdf.aiaa.org/downloads/1996/1996_3152.pdf |archive-date=2007-04-13|url-access=subscription }}</ref>