Continental T51
development of the French Turbomeca Artouste turboshaft engine built in the USA
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. 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.
Variants and derivatives
XT51-1
(Model 210) Based on the Turbomeca Artouste I; 280 shp.
XT51-3
(Model 220-2) Based on the Turbomeca Artouste II; 425 shp.
XT72
(Model 217-5) Based on the Turbomeca Astazou; 600 shp.
XT65
(Model 217-10) A scaled-down version of the Astazou; competed against the Allison T63 to power the Light Observation Helicopter; 305 shp.
T65-T-1
XT67
(Model 217A) two engines driving a common gearbox; based on the Turbomeca Astazou X and T72; 1,540 shp.
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
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
Model TS325-1
Alternative company designation for the T65-T-1
Model 327-5
Turboprop version of the T65-T-1
Applications
XT51-1
XL-19C Bird Dog
Sikorsky XH-39 (S-59)
XT51-3
Bell 201 (XH-13F)
XT67
Bell 208
XT72
Republic Lark (license-built Aérospatiale Alouette II)
Specifications (XT51-3)
Data from Aircraft engines of the World 1957
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
Turbomeca Artouste
Comparable engines
Boeing T50
Related lists
List of aircraft engines
References
Further reading
Gunston, Bill (2006).
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