Turboshaft helicopter engine
TheLycoming T53 , (company designationLTC-1 ) is aturboshaft engine used onhelicopters and (as aturboprop ) fixed-wingaircraft since the 1950s. It was designed at theLycoming Turbine Engine Division inStratford, Connecticut , by a team headed byAnselm Franz , who was the chief designer of theJunkers Jumo 004 duringWorld War II .
A much larger engine, similar in overall design, became theLycoming T55 produced byHoneywell Aerospace . The T53 model is produced by Ozark Aeroworks LLC.
Military designations [ edit ] Lycoming T53-L-1 turboshaft engine atSteven F. Udvar-Hazy Center in Virginia, USA T53-L-1 T53-L-1A 770 hp (570 kW) T53-L-1B 860 hp (640 kW) T53-L-3 T53-L-5 960 hp (720 kW) T53-L-7 T53-L-11 1,100 hp (820 kW) T53-L-13 T53-L-13B 1,400 hp (1,000 kW) improved L-11 T53-L-701 1,400 hp (1,000 kW) turboprop variant used on Mohawk and AIDC T-CH-1 T53-L-703 1,800 hp (1,300 kW) improved durability variant of the L-13B TF12 1,150 hp (860 kW) marine gas turbine fitted to prototype hydrofoil Halobates.[ 2] T5307A commercial L-7 T5309A commercial L-9A T5309B commercial L-9B T5309C similar to T5309A but with L-11 combustion chamber T5311A 1100 shp (820 kW) T5313A 1400 shp (1044 kW) commercial variant of the L-13 T5313B 1400 shp (1044 kW) commercial variant of the L-13 T5317A 1500 shp (1119 kW) improved variant of the L-13 T5317A-1 T5317B T5317BCV LTC1B-1 LTC1B-2 company designation for L-1A LTC1F-1 company designation for L-3 LTC1F-2 company designation for L-7 LTC1K-1 company designation for L-5 LTC1K-2 company designation for L-9 LTC1K-2A company designation for L-9A LTC1K-2B company designation for L-9B LTC1K-4 company designation for L-13 LTC1K-4A for tilt-wing / tilt-rotor aircraft (Canadair CL-84 Dynavert ) LTC1K-4K 1550 shp (1156 kW) direct drive variant of the L-13B LTC1K-5 company designation for L-11 Kawasaki KT5311A Kawasaki production forFuji-Bell 204B helicopters [ edit ] Data from Flight International [ 5]
General characteristics Type:Turboshaft Length: 58.4 in (1,483 mm) Diameter: 23 in (584 mm) Dry weight: 688 lb (312 kg)
Components
Performance Related development
Related lists
Gunston, Bill (2006).World Encyclopedia of Aero Engines, 5th Edition . Phoenix Mill, Gloucestershire, England, UK: Sutton Publishing Limited. p. 132.ISBN 0-7509-4479-X
