T51
The T51-powered Bell 201/XH-13F in a hover
Type	Turboshaft
National origin	United States
Manufacturer	Continental Aviation and Engineering
Major applications	Bell 201 Sikorsky XH-39
Developed from	Turbomeca Artouste

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]

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

• 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^[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)