Snecma M53#Variants

The engine was derived from the Atar series by adding a bypass duct aft of the 3rd compressor stage. The first 3 stages were enlarged to give an LP and HP section on the same shaft. It is a single shaft turbofan, or continuous bleed/bypass turbojet.{{Cite book |last=Jane |first=Frederick T. |title=Jane's All The World's Aircraft, 1975-1976 |publisher=Franklin Watts Inc. |year=1975 |isbn=0-531 03250 7 |editor-last=Taylor |editor-first=John W. R. |location=New York |pages=691}} It was originally called the Super Atar 9K50 and was designed for sustained flight at Mach 2.5.{{Cite magazine |date=1973-11-22 |title=Engines |url=https://www.flightglobal.com/pdfarchive/view/1973/1973%2520-%25202846.html?search=snecma |magazine=Flight International |page=863 |archive-url=https://web.archive.org/web/20181230032452/https://www.flightglobal.com/pdfarchive/view/1973/1973%2520-%25202846.html?search=snecma |archive-date=2018-12-30 |access-date=2021-05-30}} Flight testing started in July 1973 using a Caravelle flying test-bed and the engine first went supersonic in a Mirage F.1 test bed at the end of 1974.{{Cite magazine |date=1976-11-27 |title=France's Aircraft Industry |url=https://www.flightglobal.com/pdfarchive/view/1976/1976-2802.html?search=snecma |magazine=Flight International |page=1599 |archive-url=https://web.archive.org/web/20181230032458/https://www.flightglobal.com/pdfarchive/view/1976/1976%20-%202802.html?search=snecma |archive-date=2018-12-30 |access-date=2021-05-30}}

The engine was designed to have better performance than the latest Atar engines but simpler and less costly than the SNECMA TF 306 turbofan. The fan and HP compressor on the same shaft gave an engine with no restrictions on throttle movements, known as 'carefree handling', during flight.The Development Of Jet And Turbine Engines, Bill Gunston, Hayne's Publishing 2006, {{ISBN|0 7509 4477 3}}, p.179

The engine has a modular construction, first introduced on the Napier Eland turboprop and then later in a big way with the Pratt & Whitney JT9D engine.{{cite web |url=https://www.flightglobal.com/pdfarchive/view/1973/1973%20-%200265.html?search=snecma |title=Archived copy |website=www.flightglobal.com |access-date=12 January 2022 |archive-url=https://web.archive.org/web/20181230032444/https://www.flightglobal.com/pdfarchive/view/1973/1973%20-%200265.html?search=snecma |archive-date=30 December 2018 |url-status=dead}} Modular construction allows sub-assemblies or modules to be changed without the need for full power testing of the engine after replacement.

Modules are changed “on condition”{{cite web |url=https://www.flightglobal.com/pdfarchive/view/1967/1967%20-%202161.html |title=Archived copy |website=www.flightglobal.com |access-date=12 January 2022 |archive-url=https://web.archive.org/web/20181230032426/https://www.flightglobal.com/pdfarchive/view/1967/1967%20-%202161.html |archive-date=30 December 2018 |url-status=dead}} by monitoring deteriorating trends in performance and mechanical measurements, such as exhaust gas temperature and oil samples, and by visually assessing blade clearances and high temperature distress on internal parts using borescopes.

The engine is in service in 8 different air forces, powering the whole Mirage 2000 family of airplanes, including the latest Mirage 2000-5 and 2000-9 multirole fighters.

File:Tuyère Mirage 2000B.jpg]]

• M53-5 - powered initial Mirage 2000C models {{Cite web |title=The Dassault Mirage 2000 & 4000 |url=https://airvectors.net/avmir2k.html |website=airvectors.net}}
• Dry thrust: 54.0 kN (5,500 kgp / 12,230 lbf)
• Afterburning thrust: 86.3 kN (8,800 kgp / 19,400 lbf)
• M53-P2 - powered later Mirage 2000C models and used to upgrade earlier models
• Dry thrust: 64.7 kN (6,600 kgp / 14,500 lbf)
• Afterburning thrust: 95.1 kN (9,700 kgp / 21,400 lbf)

• Dassault Mirage 2000
• Dassault Mirage 2000N/2000D
• Dassault Mirage 4000
• Dassault Mirage F1M-53

File:M53-P2 (Modules 1-2-3-4-5-6-7-11-12).jpg

{{jetspecs

|

|type=Afterburning single-shaft turbofan

|length=5,070 mm (199.60 in)

|diameter=796 mm (31.33 in) inlet

|weight=1,515 kg (3,340 lb)

|compressor=8-stage axial compressor

|combustion=annular

|turbine=2-stage axial turbine

|fueltype=

|oilsystem=

|power=

|thrust=

• 64 kN (14,300 lbf) military thrust
• 95 kN (21,384 lbf) with afterburner

|compression=9.8:1

|bypass=0.36:1

|aircon=92 kg/s

|turbinetemp=1 327 °C

|fuelcon=

|specfuelcon=

• 0.90(kg/daN.h) military thrust
• 2.10(kg/daN.h) maximum afterburner

|thrust/weight= 6.5

}}

{{aircontent

|see also=

|related=

|lists=

• List of aircraft engines

|similar engines=

}}

{{reflist|1}}

{{Commons category|Snecma M53}}

• [http://www.snecma.com/military-engines/training-and-combat-aircraft/m53 Manufacturer website]
• [https://web.archive.org/web/20101009014438/http://www.snecma.com/IMG/pdf/M53-P2_ang-2.pdf Manufacturer Specification sheet (pdf)]

{{Snecma aeroengines}}

Category:Low-bypass turbofan engines

Category:1970s turbofan engines

M53