|
gptkbp:instance_of
|
gptkb:jet_engine
|
|
gptkbp:air_support
|
100 kg/s
|
|
gptkbp:average_temperature
|
1,500 ° C
|
|
gptkbp:certification
|
EASA certified
|
|
gptkbp:check_in_time
|
yes
|
|
gptkbp:combustor_type
|
annular combustor
|
|
gptkbp:compression_ratio
|
30:1
|
|
gptkbp:control_system
|
gptkb:FADEC
digital control system
|
|
gptkbp:cooling_system
|
gptkb:water
liquid cooling
air-cooled
|
|
gptkbp:designed_by
|
gptkb:MTU_Aero_Engines
|
|
gptkbp:diameter
|
1.2 m
1.0 m
|
|
gptkbp:elevation
|
12,000 m
|
|
gptkbp:emissions_standard
|
Euro 6
|
|
gptkbp:engine
|
gptkb:military_aircraft
upgradable
air start
|
|
gptkbp:engine_configuration
|
twin-spool
pylon-mounted
|
|
gptkbp:engine_power
|
high performance
4,000 hours
|
|
gptkbp:engine_type
|
turbofan
M53-P46 A
|
|
gptkbp:first_flight
|
gptkb:1994
|
|
gptkbp:fuel_capacity
|
3,000 liters
|
|
gptkbp:fuel_economy
|
0.5 kg/ N·h
|
|
gptkbp:fuel_type
|
gptkb:Jet_A-1
|
|
gptkbp:gearbox
|
reduction gearbox
|
|
https://www.w3.org/2000/01/rdf-schema#label
|
M53-P46 engine
|
|
gptkbp:ignition_system
|
spark ignition
|
|
gptkbp:investment
|
40 psi
|
|
gptkbp:is_tested_for
|
ground testing
|
|
gptkbp:launch_date
|
30 seconds
|
|
gptkbp:length
|
4.5 m
|
|
gptkbp:maintenance
|
1,000 hours
|
|
gptkbp:manufacturer
|
gptkb:MTU_Aero_Engines
|
|
gptkbp:max_speed
|
Mach 2.0
|
|
gptkbp:noise_level
|
85 d B
|
|
gptkbp:operational_range
|
2,500 km
|
|
gptkbp:propulsion
|
yes
6:1
jet propulsion
90 k N
|
|
gptkbp:service_ceiling
|
15,000 m
|
|
gptkbp:specific_impulse
|
300 s
|
|
gptkbp:type
|
gptkb:turbofan_engine
|
|
gptkbp:used_in
|
gptkb:Eurofighter_Typhoon
|
|
gptkbp:weight
|
1,500 kg
|
|
gptkbp:bfsParent
|
gptkb:Snecma_Propulsion
gptkb:Snecma_Moteurs
|
|
gptkbp:bfsLayer
|
6
|