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|T55-GA-714A turboshaft engine on a CH-47 Chinook|
|National origin||United States|
|Manufacturer||Lycoming Engines |
|Major applications||CH-47 Chinook |
Piper PA-48 Enforcer
|Developed from||Lycoming T53|
|Developed into||Lycoming/Vericor TF40|
The Lycoming T55 (Company designation Lycoming LTC-4) is a turboshaft engine used on American helicopters and fixed-wing aircraft (in turboprop form) since the 1950s, and in unlimited hydroplanes since the 1980s. It was designed at the Lycoming Turbine Engine Division in Stratford, Connecticut, as a scaled-up version of the smaller Lycoming T53. Both engines are now produced by Honeywell Aerospace. The T55 also serves as the core of the Lycoming ALF 502 turbofan. Since the T55 was first developed, progressive increases in airflow, overall pressure ratio, and turbine inlet temperature have more than tripled the power output of the engine.
- 1,651 shp (1,232kW)
- company designation for L-5
- company designation for L-7
- 2,970 shp (2,216 kW)
- similar to L-7 with two-stage gas generator turbine
- 4,600 shp (3,432 kW)
- company designation for L-9
- 9-stage compressor
- 2,930 shp (2,186 kW):Commercial version of the LTC4-8D
- 4,200 shp (3,133 kW)
- 2,200 shp (1,641 kW)
- 2,650 shp (1,977 kW)
- 2,595 eshp (1,936 kW)
- 3,750 shp ( 2,798 kW)
- 3,750 shp ( 2,798 kW)
- 4,110 shp (3,066 kW)
- 4,867 shp (3,631 kW)
- 6,500 shp (4,849 kW):variable vane control : under development.
- Turbofan with T55 7-stage compressor gas generator core
- Turbofan with T55 / LTC4K 9-stage compressor gas generator core
- Textron Lycoming AL5512
- civil T55
- Bell 214
- Bell 309
- Boeing CH-47 Chinook
- Boeing Chinook (UK variants)
- Boeing Model 360
- Boeing RC-135 - One T55 was fitted to the RC-135E derivative to provide power to the aircraft's phased array radar.
- Curtiss-Wright X-19
- North American YAT-28E Trojan
- Piper PA-48 Enforcer
- Sikorsky–Boeing SB-1 Defiant
- unlimited hydroplanes
- Type: Turboshaft
- Length: 1,196.3 mm (47.10 in)
- Diameter: 615.9 mm (24.25 in)
- Dry weight: 377 kg (831 lb)
- Compressor: 7-stage axial and 1-stage centrifugal
- Combustors: reverse flow
- Turbine: 2-stage gas producer and 2-stage free power
- Maximum power output: 4,867 shp (3,629 kW)
- Overall pressure ratio: 9.32
- Turbine inlet temperature: 815 °C (1,499 °F) (power turbine inlet temperature)
- Power-to-weight ratio: (4,867 shp / 831 lbs) ~ 5.8568:1 shp/lb
- "sherpa | college | aeronautics | 1957 | 0430 | Flight Archive". Flightglobal.com. Retrieved 2019-02-09.
- "helicopter engine | american airlines | dry weight | 1959 | 0813 | Flight Archive". Flightglobal.com. Retrieved 2019-02-09.
- "1996 | 2830 | Flight Archive". Flightglobal.com. 1996-10-29. Retrieved 2019-02-09.
- "CH-47D Power Plants (714) (AQC/IPC/MOI/FEIC)" (PDF).
- 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.
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