Editing Engine Alliance GP7000 (section)

==Specifications (GP7270)==
{{jetspecs
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|type          = two-spool high-bypass [[turbofan]] engine
|length        = {{convert|4.92|m|ft in|abbr=on}} spinner to flange<ref>[https://www.easa.europa.eu/system/files/dfu/20140404_TCDS_IM.E.026_issue04_0.pdf EASA Type certificate data sheet] European Aviation Safety Agency 4 April 2014 {{webarchive|date=23 December 2017
|url=https://web.archive.org/web/20171223075120/https://www.easa.europa.eu/system/files/dfu/20140404_TCDS_IM.E.026_issue04_0.pdf}}</ref>
|diameter  = {{convert|3.16|m|ft in|abbr=on}}, fan {{convert|2.96|m|ft in|abbr=on}}
|weight        = {{convert|6712|kg|lb|abbr=on}}
|compressor    = 24 swept [[Wide chord|wide-chord]] hollow titanium fan blades, 8.8:1 by-pass ratio; five-stage low-pressure [[axial compressor]]; nine-stage high-pressure axial compressor
|combustion    = low-emissions single annular combustor 
|turbine       = two-stage high pressure turbine, boltless architecture, single crystal blades, split blade cooling and thermal barrier coatings, axial flow; six-stage low-pressure axial flow
|fueltype      =
|oilsystem     =
|compression   = 43.9
|aircon       = 900 to 1,200 kg/s (2,000 to 2,600 lb/s)
|fuelcon       =
|specfuelcon   =
|thrust= 36,980 kgf, 363 kN, 81,500 lbf
|thrust/weight = 5.197 (assuming 13,400 lbf weight of engine and 70,000 lbf of thrust)
}}