View source for Engine pressure ratio

The '''engine pressure ratio''' ('''EPR''') is the total pressure ratio across a [[jet engine]], measured as the ratio of the total pressure at the exit of the propelling nozzle divided by the total pressure at the entry to the compressor.<ref>{{cite web|url=http://www.grc.nasa.gov/WWW/k-12/airplane/epr.html | title=Pressure variation - EPR | access-date=January 2, 2015 | author=Glenn Research Center (NASA)}}</ref>

Jet engines use either EPR or compressor/fan RPM as an indicator of thrust.<ref>{{cite web |url=http://code7700.com/epr.html |title=Engine Pressure Ratio (EPR) |website=code7700.com |url-status=dead |archive-url=https://web.archive.org/web/20141004201047/http://code7700.com/epr.html |archive-date=2014-10-04}}</ref> When EPR is used, the pressures are measured in front of the compressor and behind the turbine.

== Integrated engine pressure ratio ==

The integrated engine pressure ratio (IEPR) is a ratio used on some [[turbofan]]s to include fan discharge total pressure and compressor inlet total pressure. If compressor inlet pressure is P0 and fan discharge total pressure is P1, then the integrated engine pressure ratio will be P1 /P0.<ref>{{cite web|url= https://aviation_dictionary.en-academic.com/3854/integrated_engine_pressure_ratio |title= integrated engine pressure ratio |publisher= aviation_dictionary.en-academic.com |access-date=2023-06-07}}</ref>

The IEPR is an engine indicator system unique to the [[Rolls-Royce RB211]].

== See also ==
*[[Jet engine performance]]
*[[Turbofan]]

== References ==
{{Reflist}}
* The Boeing Company '' Engine thrust control system '' [https://patents.google.com/patent/US4248042 US Patent 4248042] Includes [[Boeing]]'s discussion on EPR or IEPR being a better indicator of thrust.

== External links ==
* [http://www.grc.nasa.gov/WWW/K-12/airplane/epr.html Pressure Variation EPR - NASA Animation]

{{Aircraft gas turbine engine components}}

[[Category:Engineering ratios]]
[[Category:Aircraft engines]]


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