Lycoming T53

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Lycoming T53 (left output via reduction gear, older variant with two turbine stages)

The Lycoming T53 (factory designation LTC1 ) is a shaft turbine made by the US manufacturer Lycoming , which has been used in helicopters and fixed-wing aircraft since the 1950s, as well as in eight diesel locomotives of the German Federal Railroad . A scaled-up development based on the T53 is the T55 .

history

The engine was designed by Anselm Franz , who was responsible for developing the Jumo 004 during World War II . The T53 was developed against the background of a joint contract between Lycoming and the US Air Force and the US Army , and around 19,000 copies were produced by 1993. By then, a total of around 46 million operating hours had been accumulated.

Manufacturing licenses are held by Rolls-Royce Germany , Piaggio in Italy and Kawasaki in Japan.

To date, Rolls-Royce has manufactured over 420 of these T53 engines for the German armed forces. The company also provides repair and overhaul, as well as technical and logistical services for this engine.

Versions

T53-L-1A and L-1B
Basic version for helicopters, 645 kW (860 WPS)
T53-L-3
Propeller turbine for fixed wing aircraft, 739 kW (1005 WPS)
T53-L-5
Helicopter turbine, 739 kW (1005 WPS)
T53-L-7
for fixed wing aircraft, 846 kW (1150 WPS)
T53-L-9
for helicopters, 846 kW (1150 WPS)
T53-L-11
615 kW (825 WPS)
T53-L-13
first variant with four turbine stages instead of two in the earlier versions. Different fuels can be used. Used in the Bell UH-1 M, UH-1H and AH-1F HueyCobra and on a trial basis in eight diesel locomotives of the DB class 210
T5312A and B
Versions for civil use
T53-L-701
"Split Power" reduction gear, 1044 kW (1400 WPS)
T53-L-703
Improved long-term durability, 1343 kW (1800 WPS)
LTC1K-4K
L-13 with direct drive, installation is possible for operation inclined between 105 ° upwards and 90 ° downwards.
T5317A
improved L-13

commitment

Technical specifications

Apply to version L-13 and L-701

Parameter Data
Type Shaft turbine (with free-running output shaft)
compressor Five-stage axial compressor and single-stage centrifugal compressor. Compression ratio 7.2: 1, mass flow: 5.53 kg / s at a speed of 21,150 min −1 of the turbine part.
Combustion chamber Annular combustion chamber with reversal of the gas flow, 22 injection nozzles
fuel ASTM A-1 , MIL-J-5624, MIL-F-26005A, JP-1 , JP-4 , JP-5 , CITE
turbine Four-stage axial turbine; two stages drive the compressors and two stages act on the reduction gear. The output shaft (output) is usually located at the front, but can also optionally be located at the rear.
Max. Diameter 0.584 m
length 1.209 m
Weight (dry) 312 kg
Nominal shaft power 1082 kW (1451 WPS)

literature

  • Mark Lambert (Ed.): Jane's All The World's Aircraft - 1993-94. Jane's Information Group Ltd., Coulsdon 1993.

Individual evidence

  1. ↑ Jane's 1993-94, p. 680

Web links

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