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gptkbp:instance_of
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gptkb:turbofan_engine
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gptkbp:application
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helicopters
civil and military aviation
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gptkbp:average_temperature
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-40 to 50 ° C
up to 800 ° C
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gptkbp:certification
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gptkb:EASA
EASA certified
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gptkbp:combustor_type
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annular
annular combustion chamber
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gptkbp:compression_ratio
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10:1
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gptkbp:compressor_stage
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gptkb:1
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gptkbp:compressor_type
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centrifugal compressor
axial compressor
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gptkbp:control_system
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electronic control unit
hydromechanical
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gptkbp:cooling_system
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air-cooled
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gptkbp:country_of_origin
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gptkb:France
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gptkbp:design
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gptkb:Turbomeca
modular design
Turbomeca design team
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gptkbp:development
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Turbomeca Astazou was developed in the 1950s.
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gptkbp:diameter
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0.4 m
400 mm
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gptkbp:emissions_standard
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low emissions
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gptkbp:engine
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gptkb:turbofan_engine
gptkb:Turbomeca_TM_319
gptkb:Turbomeca_Artouste
starter motor
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gptkbp:engine_configuration
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gptkb:1
horizontal
free turbine
flexible mount
twin-shaft
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gptkbp:engine_power
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high
30%
3,000 hours
2,000 hours
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gptkbp:engine_type
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gptkb:Astazou_IV
gptkb:Astazou_1_B
gptkb:Astazou_1_C
gptkb:Astazou_1_D
gptkb:Astazou_1_E
gptkb:Astazou_1_F
gptkb:Astazou_1_G
gptkb:Astazou_1_H
gptkb:Astazou_1_I
gptkb:Astazou_1_J
gptkb:Astazou_1_K
gptkb:Astazou_1_N
gptkb:Astazou_1_P
gptkb:Astazou_1_Q
gptkb:Astazou_1_S
gptkb:Astazou_1_T
gptkb:Astazou_1_U
gptkb:Astazou_1_W
gptkb:Astazou_1_X
gptkb:Astazou_1_Y
gptkb:Astazou_1_Z
gptkb:Astazou_50
gptkb:Astazou_V
gptkb:Astazou_II
gptkb:Astazou_III
Astazou 1 L
Astazou 1 M
Astazou 1 O
Astazou 1 R
Astazou 1 V
Astazou 14
Astazou 16
Astazou 18
Astazou 20
Astazou 22
Astazou 24
Astazou 26
Astazou 28
Astazou 30
Astazou 32
Astazou 34
Astazou 36
Astazou 38
Astazou 40
Astazou 42
Astazou 44
Astazou 46
Astazou 48
Astazou VI
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gptkbp:exhaust_system
|
gptkb:straight
|
|
gptkbp:first_flight
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gptkb:1956
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|
gptkbp:fuel_capacity
|
0.5 m
1.5 m
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|
gptkbp:fuel_economy
|
high fuel efficiency
0.5 kg/k W·h
0.5 kg/k W/h
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gptkbp:fuel_type
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gptkb:Jet_A-1
dual fuel system
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gptkbp:gearbox
|
reduction gearbox
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https://www.w3.org/2000/01/rdf-schema#label
|
Turbomeca Astazou
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gptkbp:ignition_system
|
spark ignition
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gptkbp:launch_window
|
starter motor
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gptkbp:length
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1.2 m
1,200 mm
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gptkbp:maintenance
|
scheduled maintenance
500 hours
1,500 hours
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gptkbp:manufacturer
|
gptkb:Turbomeca
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gptkbp:noise_level
|
85 d B
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gptkbp:notable_users
|
gptkb:French_Army
gptkb:Indian_Air_Force
gptkb:Brazilian_Army
gptkb:Aérospatiale
gptkb:Spanish_Army
gptkb:Eurocopter_AS350_Écureuil
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|
gptkbp:number_of_stages
|
2
|
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gptkbp:operational_history
|
used in military and civilian applications.
|
|
gptkbp:operational_range
|
1,000 km
up to 1,000 km
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|
gptkbp:power_output
|
370 k W
|
|
gptkbp:powers
|
3.1 k W/kg
|
|
gptkbp:propulsion
|
mechanical propulsion
500 to 1,000 lbf
500 to 600 lbf
|
|
gptkbp:reliability
|
high
high reliability
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gptkbp:service
|
up to 5,000 hours
|
|
gptkbp:service_ceiling
|
3,000 m
|
|
gptkbp:service_entry
|
gptkb:1960
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gptkbp:successor
|
gptkb:Turbomeca_Arriel
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|
gptkbp:turbine_stage
|
gptkb:1
|
|
gptkbp:turbine_type
|
free turbine
single-stage turbine
nickel alloy
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gptkbp:type
|
gptkb:turbofan_engine
|
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gptkbp:used_in
|
gptkb:Aérospatiale_SA_315_Lama
|
|
gptkbp:variant
|
gptkb:Astazou_II
gptkb:Astazou_III
|
|
gptkbp:weight
|
120 kg
|
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gptkbp:bfsParent
|
gptkb:IAR_330_Puma
gptkb:Rolls-Royce_Turbomeca_Adour
gptkb:IAR_316_Alouette_III
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gptkbp:bfsLayer
|
6
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