|
gptkbp:instance_of
|
gptkb:turbofan_engine
|
|
gptkbp:application
|
gptkb:helicopter
|
|
gptkbp:average_temperature
|
up to 1,500 ° F
|
|
gptkbp:certification
|
FAA certified
|
|
gptkbp:compression_ratio
|
8:1
|
|
gptkbp:compressor_type
|
aluminum alloy
single-stage centrifugal compressor
|
|
gptkbp:configuration
|
free turbine
|
|
gptkbp:control_system
|
gptkb:full_authority_digital_engine_control_(FADEC)
hydraulic control system
|
|
gptkbp:cooling_system
|
air-cooled
|
|
gptkbp:development
|
1950s
|
|
gptkbp:diameter
|
approximately 15 in
|
|
gptkbp:emissions_standard
|
EPA Tier 4
|
|
gptkbp:engine
|
gptkb:Lycoming_T53-L-13
gptkb:Lycoming_T53-L-703
Brayton cycle
|
|
gptkbp:engine_configuration
|
modular design
mounts on helicopter frame
|
|
gptkbp:engine_type
|
gptkb:turbofan_engine
|
|
gptkbp:exhaust_system
|
single exhaust
|
|
gptkbp:first_flight
|
gptkb:1960
|
|
gptkbp:fuel_capacity
|
dry sump
|
|
gptkbp:fuel_economy
|
0.5 lb/hp/hr
|
|
gptkbp:fuel_tank_location
|
under fuselage
|
|
gptkbp:fuel_type
|
gptkb:Jet_A
dual fuel pumps
|
|
https://www.w3.org/2000/01/rdf-schema#label
|
Lycoming T53-L-35
|
|
gptkbp:ignition_system
|
dual ignition
|
|
gptkbp:is_tested_for
|
ground testing required
|
|
gptkbp:launch_window
|
air start
|
|
gptkbp:length
|
approximately 40 in
|
|
gptkbp:maintenance
|
500 hours
|
|
gptkbp:manufacturer
|
gptkb:Lycoming_Engines
|
|
gptkbp:market_segment
|
gptkb:military_aircraft
|
|
gptkbp:max_speed
|
42,000 rpm
|
|
gptkbp:noise_level
|
85 d B
|
|
gptkbp:operational_range
|
up to 30,000 ft
|
|
gptkbp:power_output
|
1,400 shp
|
|
gptkbp:predecessor
|
gptkb:Lycoming_T53-L-13
|
|
gptkbp:propulsion
|
1,400 lbf
4.67 shp/lb
|
|
gptkbp:service
|
up to 5,000 hours
|
|
gptkbp:successor
|
gptkb:Lycoming_T53-L-703
|
|
gptkbp:turbine_type
|
two-stage turbine
nickel-based superalloy
|
|
gptkbp:type
|
gptkb:turbofan_engine
|
|
gptkbp:used_in
|
gptkb:Bell_UH-1_Iroquois
|
|
gptkbp:weight
|
approximately 300 lb
|
|
gptkbp:bfsParent
|
gptkb:Lycoming_T53-L-13
|
|
gptkbp:bfsLayer
|
7
|