Lycoming T55
"T55" redirects here. For the American utility carrier prototype see M50 Ontos, and for the Soviet tank, see T-54/55.
| T55 | |
|---|---|
 | |
| T55-GA-714A turboshaft engine on a CH-47 Chinook | |
| Type | Turboshaft |
| National origin | United States |
| Manufacturer | Lycoming Engines Honeywell Aerospace |
| First run | 1950s |
| Major applications | CH-47 Chinook Bell 309 Piper PA-48 Enforcer |
| Number built | 4,200+ |
| 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. 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][2][3]
Variants
- LTC4A-1
- 1,651 eshp (1,232kW)
- LTC4B-8D
- 2,970 shp (2,216 kW)
- LTC4B-12
- 4,600 shp (3,432 kW)
- T5508D
- 2,930 shp (2,186 kW):Commercial version of the LTC4-8D
- AL5512
- 4,200 shp (3,133 kW)
- T55-L-5
- 2,200 shp (1,641 kW)
- T55-L-7
- 2,650 shp (1,977 kW)
- T55-L-9
- 2,595 eshp (1,936 kW)
- T55-L-11
- 3,750 shp ( 2,798 kW)
- T55-L-712
- 3,750 shp ( 2,798 kW)
- T55-L-714
- 4,110 shp (3,066 kW)
- T55-L-714A
- 4,867 shp (3,631 kW)
- T55-GA-715
- 6,500 shp (4,849 kW):variable vane control : under development.
Applications
- 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
- H1 Unlimited hydroplane
Specifications (T55-L-714A)
General characteristics
- Type: Turboshaft
- Length: 1,196.3 mm (47.1 inches)
- Diameter: 615.9 mm (24.3 inches)
- Dry weight: 377kg (831 lbs)
Components
- Compressor: 7-stage axial compressor and 1-stage centrifugal compressor
- Combustors: reverse flow
- Turbine: 2-stage gas producer and 2-stage free power
Performance
- Maximum power output: 4,867 shp (3,631 kW)
- Overall pressure ratio: 9.32[4]
- Turbine inlet temperature: 815 °C (power turbine inlet temperature)
- Power-to-weight ratio: (4,867 shp / 831 lbs) ~ 5.8568:1 shp/lb
See also
- Comparable engines
- Related lists
References
- ↑ https://www.flightglobal.com/pdfarchive/view/1957/1957%20-%200430.html?search=T55
- ↑ https://www.flightglobal.com/pdfarchive/view/1959/1959%20-%200813.html?search=T55
- ↑ https://www.flightglobal.com/pdfarchive/view/1996/1996%20-%202830.html?search=T55-L-714A
- ↑ "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.
External links
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