|
gptkbp:instance_of
|
gptkb:turbofan_engine
|
|
gptkbp:air_support
|
80 kg/s
|
|
gptkbp:application
|
gptkb:military_aircraft
|
|
gptkbp:average_temperature
|
up to 1,600 ° C
|
|
gptkbp:combustor_type
|
annular
|
|
gptkbp:compressor_type
|
gptkb:5
|
|
gptkbp:control_system
|
gptkb:FADEC
digital
|
|
gptkbp:cooling_system
|
air-cooled
|
|
gptkbp:design
|
modular
|
|
gptkbp:development
|
gptkb:Snecma_M88
|
|
gptkbp:diameter
|
0.9 m
|
|
gptkbp:emissions_standard
|
low
|
|
gptkbp:engine
|
gptkb:Snecma_M88-3
gptkb:military_aircraft
gptkb:Snecma_M88
air-start
|
|
gptkbp:engine_configuration
|
modular
twin-spool
|
|
gptkbp:engine_operating_temperature
|
up to 1,600 ° C
|
|
gptkbp:engine_power
|
high
70 k N with afterburner
|
|
gptkbp:engine_turbine_material
|
ceramic matrix composites
|
|
gptkbp:engine_type
|
turbofan
|
|
gptkbp:first_flight
|
gptkb:1986
|
|
gptkbp:fuel_capacity
|
0.9 m
1,200 kg
3.8 m
|
|
gptkbp:fuel_economy
|
high
0.85 kg/k N/h
|
|
gptkbp:fuel_type
|
gptkb:Jet_A-1
|
|
https://www.w3.org/2000/01/rdf-schema#label
|
Snecma M88-2
|
|
gptkbp:length
|
3.8 m
|
|
gptkbp:maintenance
|
1,500 hours
|
|
gptkbp:manufacturer
|
gptkb:Snecma
|
|
gptkbp:max_speed
|
Mach 1.8
|
|
gptkbp:noise_level
|
low
|
|
gptkbp:number_of_stages
|
gptkb:3
|
|
gptkbp:operational_range
|
1,000 km
|
|
gptkbp:propulsion
|
yes
50 k N
|
|
gptkbp:service_entry
|
gptkb:2001
|
|
gptkbp:turbine_type
|
2
ceramic matrix composites
|
|
gptkbp:type
|
afterburning turbofan
|
|
gptkbp:used_in
|
gptkb:Dassault_Rafale
|
|
gptkbp:video_output
|
axial
|
|
gptkbp:weight
|
1,200 kg
|
|
gptkbp:bfsParent
|
gptkb:Snecma_M88
|
|
gptkbp:bfsLayer
|
5
|