|
gptkbp:instance_of
|
gptkb:engine
|
|
gptkbp:bfsLayer
|
7
|
|
gptkbp:bfsParent
|
gptkb:Lycoming_T53-L-703
gptkb:Lycoming_T53-L-91
|
|
gptkbp:application
|
gptkb:helicopter
|
|
gptkbp:average_temperature
|
up to 1,000 ° F
1,200 ° F
|
|
gptkbp:certification
|
military certification required
|
|
gptkbp:compression_ratio
|
8:1
|
|
gptkbp:controls
|
digital control system
hydromechanical fuel control
|
|
gptkbp:cooling_system
|
air-cooled
|
|
gptkbp:diameter
|
approximately 14 in
|
|
gptkbp:drivetrain
|
reduction gearbox
|
|
gptkbp:emissions_standard
|
meets military standards
axial flow
straight exhaust
|
|
gptkbp:engine
|
single rotor
twin-spool
flexible mount
2,000 hours
|
|
gptkbp:engine_type
|
aluminum alloy
free turbine
two-stage turbine
turbo-shaft
nickel-based superalloy
three-stage compressor
|
|
gptkbp:features
|
modular design
|
|
gptkbp:first_flight
|
gptkb:1960
|
|
gptkbp:fuel_capacity
|
0.5 lb/hp/hr
40 in length, 14 in diameter
|
|
gptkbp:fuel_type
|
gptkb:Jet_A
gptkb:railway_station
annular combustion chamber
dual fuel system
|
|
https://www.w3.org/2000/01/rdf-schema#label
|
Lycoming T53-L-747
|
|
gptkbp:ignition_system
|
spark ignition
|
|
gptkbp:is_tested_for
|
ground testing required
|
|
gptkbp:launched
|
starter-generator
|
|
gptkbp:length
|
approximately 40 in
|
|
gptkbp:maintenance
|
500 hours
|
|
gptkbp:manufacturer
|
gptkb:Lycoming_Engines
|
|
gptkbp:max_speed
|
30,000 rpm
|
|
gptkbp:operational_history
|
used in various military applications
|
|
gptkbp:power_output
|
1,400 shp
|
|
gptkbp:propulsion
|
3.5:1
1,400 lbf
3.5 hp/lb
|
|
gptkbp:service_ceiling
|
20,000 ft
|
|
gptkbp:type
|
gptkb:engine
|
|
gptkbp:used_in
|
gptkb:Bell_UH-1_Iroquois
|
|
gptkbp:variant
|
T53-L-703
|
|
gptkbp:water_source
|
300 lb/hr
|
|
gptkbp:weight
|
400 lb
approximately 400 lb
|