Continental_T51 Knowpia

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 edit

Cessna XL-19C Bird Dog

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 edit

Sikorsky S-59 on display at the New England Air Museum

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) edit

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)

References edit

^ ^a ^b ^c ^d ^e ^f ^g 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.
^ ^a ^b ^c ^d ^e Wilkinson, Paul H. (1966). Aircraft engines of the World 1966/77 (21st ed.). London: Sir Isaac Pitman & Sons Ltd. pp. 78–79.
^ Wilkinson, Paul H. (1957). Aircraft engines of the World 1957 (13th ed.). London: Sir Isaac Pitman & Sons Ltd. p. 52.