Boeing T50

T50
Type	Turboshaft
National origin	United States
Manufacturer	Boeing
Major applications	QH-50 DASH
Developed into	Boeing T60

The Boeing T50 (company designation Model 502) was a small turboshaft engine produced by Boeing. It was the first turboshaft engine to ever power a helicopter: a modified Kaman K-225 in 1951. Based on Boeing's earlier Model 500 gas generator, the T50's main application was in the QH-50 DASH helicopter drone of the 1950s. An up-rated version designated Model 550 was developed to power the QH-50D and was given the military designation T50-BO-12.

Two T50 were tested on a HTK-1 (Kaman HH-43 Huskie) in the 1950s, which was the first test of twin turbine engine on a helicopter.

Variants

T50-BO-1

T50-BO-2

T50-BO-4

270 hp (201.34 kW) at 6,000 output rpm, military rating turboprop.

T50-BO-6

T50-BO-8

300 hp (223.71 kW) at 5,950 output rpm, revised reduction gear ratio, fuelsystem and other changes.

T50-BO-8A

T50-BO-10

330 hp (246.08 kW) at 6,000 output rpm

T50-BO-12

502-1-1

Auxiliary power unit

502-2E

Turboprop, 175 hp (130.50 kW) at 2,900 output rpm max. continuous at sea level.

502-7B

Compressed air generator.

502-8A

Turboshaft.

502-8B

Turboprop, 210 hp (156.60 kW) at 37,500 compressor rpm for take-off.

502-10B

Turboprop, 270 hp (201.34 kW) at 37,500 compressor rpm for take-off.

502-10C

Turboshaft power unit / gas producer

502-10F

502-10V

(T50-BO-4)

502-10VB

325 hp (242.35 kW) at 3,000 output rpm, variant of -10V / T50-B0-4 with revised reduction gear ratio.

502-10VC

(T50-BO-8)

502-11

Compressed air generator.

502-11B

502-12B

502-W

502-14

(T50-BO-10)

550-1

(T50-BO-12)

Applications

T50 (Model 502)

• Gyrodyne QH-50 DASH
• Kaman K-225
• Kaman HTK-1
• Kaman K-1125
• XL-19B Bird Dog
• Radioplane RP-77D

GT502

• Stridsvagn 103

Specifications (T50-BO-10 / 502-14)

A QH-50D anti-submarine drone aboard the USS Allen M. Sumner (DD-692) in the late 1960s, with the T50 engine visible on the right

Data from Jane's All the World's Aircraft 1962-63.

General characteristics

• Type: Turboshaft
• Length: 37.2 in (945 mm)
• Diameter: 22.5 in (572 mm)
• Dry weight: 215 lb (98 kg)

Components

• Compressor: Single-stage centrifugal flow
• Combustors: 2 can combustors
• Turbine: 1 axial gas generator power turbine stage and 1 axial free-power turbine stage
• Fuel type: Aviation kerosene
• Oil system: pressure spray/splash, oil specification: MIL-L-7808

Performance

• Maximum power output: 330 hp (246.08 kW) military rating at 6,000 output shaft rpm
• Overall pressure ratio: 4.35:1
• Air mass flow: (4.1 lb (2 kg))/s
• Turbine inlet temperature: Jet pipe Temperature: 1,140 °F (616 °C)
• Specific fuel consumption: 0.87 lb/(hp h) (0.532 kg/(kW h))
• Power-to-weight ratio: 1.535 hp/lb (2.523 kW/kg)

See also

• Rover 1S60

Related development

• Boeing T60

Related lists

• List of aircraft engines

References

Bibliography

• Taylor, John W.R. FRHistS. ARAeS (1962). Jane's All the World's Aircraft 1962-63. London: Sampson, Low, Marston & Co Ltd.
• Gunston, Bill (2006). World Encyclopedia of Aero Engines, 5th Edition. Phoenix Mill, Gloucestershire, England, UK: Sutton Publishing Limited. p. 79. ISBN 0-7509-4479-X.
• Leyes II, Richard A.; William A. Fleming (1999). The History of North American Small Gas Turbine Aircraft Engines. Washington, DC: Smithsonian Institution. ISBN 1-56347-332-1.

External links

• Boeing Model 502 Gas Turbine Engine
• "Jet Sheds Weigh" , September 1947, Popular Science article at bottom of page on earlier Model 500