Statements (83)
| Predicate | Object |
|---|---|
| gptkbp:instance_of |
gptkb:engine
|
| gptkbp:application |
gptkb:helicopter
|
| gptkbp:average_temperature |
up to 1,000 ° F
|
| gptkbp:compression_ratio |
8:1
|
| gptkbp:cooling_system |
air-cooled
|
| gptkbp:design |
military helicopter propulsion
|
| gptkbp:developer |
1950s
|
| gptkbp:diameter |
approximately 14 in
|
| gptkbp:drivetrain |
reduction gearbox
|
| gptkbp:emissions_standard |
low emissions
axial exhaust |
| gptkbp:engine |
Brayton cycle
T53-L-13 T53-L-701 T53-L-11 T53-L-703 T53-L-1 T53-L-17 T53-L-19 T53 family T53-L-23 T53-L-25 T53-L-27 T53-L-29 T53-L-31 T53-L-33 T53-L-35 T53-L-37 T53-L-39 T53-L-41 T53-L-43 T53-L-45 T53-L-47 T53-L-49 T53-L-51 T53-L-53 T53-L-55 T53-L-57 T53-L-59 T53-L-61 T53-L-63 T53-L-65 T53-L-67 T53-L-69 T53-L-71 T53-L-73 T53-L-75 T53-L-77 T53-L-79 T53-L-81 T53-L-83 T53-L-85 T53-L-87 T53-L-89 T53-L-91 T53-L-93 T53-L-95 T53-L-97 T53-L-99 |
| gptkbp:engine_type |
centrifugal compressor
single-stage turbine |
| gptkbp:first_flight |
gptkb:1960
|
| gptkbp:fuel_capacity |
high efficiency
|
| gptkbp:fuel_type |
gptkb:Jet_A
hydromechanical fuel control system |
| https://www.w3.org/2000/01/rdf-schema#label |
Lycoming T53-L-21
|
| gptkbp:launched |
starter-generator
|
| gptkbp:length |
approximately 40 in
|
| gptkbp:maintenance |
500 hours
|
| gptkbp:manufacturer |
gptkb:Lycoming_Engines
|
| gptkbp:max_speed |
42,000 rpm
|
| gptkbp:noise_level |
moderate noise
|
| gptkbp:power_output |
1,400 shp
|
| gptkbp:propulsion |
1,400 lbf
|
| gptkbp:reliability |
high reliability
|
| gptkbp:service_history |
used in various military applications
|
| gptkbp:setting |
twin-spool
|
| gptkbp:successor |
T53-L-703
|
| gptkbp:type |
gptkb:engine
|
| gptkbp:used_in |
gptkb:Bell_UH-1_Iroquois
|
| gptkbp:weight |
approximately 300 lb
|
| gptkbp:bfsParent |
gptkb:Lycoming_T53-L-13
|
| gptkbp:bfsLayer |
6
|