Continental T51

The Continental CAE T51 was a small turboshaft engine produced by Continental Aviation and Engineering (CAE) under license from Turbomeca. A development of the Artouste, it was followed by three additional turboshaft engines, the T72, the T65, and the T67.[1] However, none of these engines, including the T51, entered full production. CAE abandoned turboshaft development in 1967 after the XT67 lost to the Pratt & Whitney Canada PT6T (T400) to power the Bell UH-1N Twin Huey.[1]

T51
The T51-powered Bell 201/XH-13F in a hover
Type Turboshaft
National origin United States
Manufacturer Continental Aviation and Engineering
Developed from Turbomeca Artouste

Variants and derivatives
XT51-1
(Model 210) Based on the Turbomeca Artouste I; 280 shp.[1]
XT51-3
(Model 220-2) Based on the Turbomeca Artouste II; 425 shp.[1]
XT72
(Model 217-5) Based on the Turbomeca Astazou; 600 shp.[1]
XT65
(Model 217-10) A scaled-down version of the Astazou; competed against the Allison T63 to power the Light Observation Helicopter; 305 shp.[1]
T65-T-1
[2]
XT67
(Model 217A) two engines driving a common gearbox; based on the Turbomeca Astazou X and T72; 1,540 shp.[1]
Model 210
Company designation for the XT51-1
Model 217-5
Company designation for the XT72
Model 217-10
Company designation for the XT65
Model 217A
Company designation for the XT67
Model 217A-2A
Company designation for the T67-T-1[2]
Model 219
similar to 220-2 with extra axial compressor stage
Model 220-2
Company designation for the XT51-3
Model 227-4A
Company designation for the T65-T-1[2]
Model TS325-1
Alternative company designation for the T65-T-1[2]
Model 327-5
Turboprop version of the T65-T-1[2]

Applications
XT51-1
XT51-3
XT67
XT72

Specifications (XT51-3)

Data from Aircraft engines of the World 1957[3]

General characteristics

  • Type: Turboshaft
  • Length: 45.1 in (1,150 mm)
  • Width:17.8 in (450 mm)
  • Height:21.5 in (550 mm)
  • Diameter:
  • Dry weight: 236 lb (107 kg)

Components

  • Compressor: 1-stage centrifugal flow
  • Combustors: annular compustion chamber
  • Turbine: 2-stage axial flow
  • Fuel type: JP-4
  • Oil system: pressure spray at 20 psi (140 kPa)

Performance

  • Maximum power output:
  • Maximum power:425 shp (317 kW) at 34,800 rpm at sea level
  • Maximum continuous power:375 shp (280 kW)at 34,800 rpm at sea level
  • Overall pressure ratio: 3.9:1
  • Air mass flow: 7 lb/s (190 kg/min)
  • Turbine inlet temperature: TIT : 1,093.15 K (1,508.00 °F; 820.00 °C); JPT: : 838.15 K (1,049.00 °F; 565.00 °C)
  • Fuel consumption: 370 lb/h (170 kg/h)
  • Thrust-to-weight ratio: 1.887 lbf/shp (11.26 N/kW)

See also

Related development

Comparable engines

Related lists

References
  1. Leyes II, Richard A.; William A. Fleming (1999). The History of North American Small Gas Turbine Aircraft Engines. Washington, DC: Smithsonian Institution. pp. 113–121. ISBN 1-56347-332-1.
  2. Wilkinson, Paul H. (1966). Aircraft engines of the World 1966/77 (21st ed.). London: Sir Isaac Pitman & Sons Ltd. pp. 78–79.
  3. Wilkinson, Paul H. (1957). Aircraft engines of the World 1957 (13th ed.). London: Sir Isaac Pitman & Sons Ltd. p. 52.

Further reading
  • Gunston, Bill (2006). World Encyclopedia of Aero Engines, 5th Edition. Phoenix Mill, Gloucestershire, England, UK: Sutton Publishing Limited. ISBN 0-7509-4479-X.
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