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gptkbp:instance_of
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gptkb:engine
|
|
gptkbp:bfsLayer
|
7
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|
gptkbp:bfsParent
|
gptkb:Lycoming_T53-L-703
gptkb:Lycoming_T53-L-91
|
|
gptkbp:application
|
gptkb:helicopter
|
|
gptkbp:average_temperature
|
high operating temperature
|
|
gptkbp:compression_ratio
|
8:1
|
|
gptkbp:controls
|
gptkb:full_authority_digital_engine_control_(FADEC)
electronic control system
|
|
gptkbp:cooling_system
|
air-cooled
air cooling
|
|
gptkbp:design
|
designed for military applications
|
|
gptkbp:developer
|
developed in the 1950s
|
|
gptkbp:diameter
|
approximately 14 in
|
|
gptkbp:drivetrain
|
integrated reduction gearbox
|
|
gptkbp:emissions_standard
|
low emissions
single exhaust outlet
|
|
gptkbp:engine
|
Brayton cycle
flexible engine mount
|
|
gptkbp:engine_type
|
gptkb:engine
two turbine stages
single stage centrifugal compressor
|
|
gptkbp:first_flight
|
gptkb:1960
|
|
gptkbp:fuel_capacity
|
moderate fuel efficiency
integrated fuel tank
approximately 0.5 lb/hp/hr
|
|
gptkbp:fuel_type
|
gptkb:Jet_A
annular combustion chamber
fuel control unit
|
|
https://www.w3.org/2000/01/rdf-schema#label
|
Lycoming T53-L-714
|
|
gptkbp:ignition_system
|
dual ignition system
|
|
gptkbp:investment
|
high pressure operation
|
|
gptkbp:launch_site
|
starter-generator system
|
|
gptkbp:length
|
approximately 40 in
|
|
gptkbp:maintenance
|
requires regular maintenance
|
|
gptkbp:manufacturer
|
gptkb:Lycoming_Engines
|
|
gptkbp:noise_level
|
moderate noise level
|
|
gptkbp:operational_history
|
widely used in the Vietnam War
|
|
gptkbp:operational_range
|
various operational ranges
|
|
gptkbp:power_output
|
1,400 shp
used in various helicopters
|
|
gptkbp:propulsion
|
4.67 shp/lb
1,400 lb thrust
|
|
gptkbp:reliability
|
high reliability
|
|
gptkbp:service_ceiling
|
15,000 ft
|
|
gptkbp:setting
|
free turbine
|
|
gptkbp:successor
|
T53-L-719
|
|
gptkbp:type
|
gptkb:engine
|
|
gptkbp:used_in
|
gptkb:Bell_UH-1_Iroquois
|
|
gptkbp:variant
|
T53-L-703
|
|
gptkbp:weight
|
approximately 300 lb
|