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Boeing T50

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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.[1] 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.

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

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.[2]

Variants

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T50-BO-1
T50-BO-2
T50-BO-4
270 hp (201.34 kW) at 6,000 output rpm, military rating turboprop.[3]
T50-BO-6
T50-BO-8
300 hp (223.71 kW) at 5,950 output rpm, revised reduction gear ratio, fuelsystem and other changes.[3]
T50-BO-8A
T50-BO-10
330 hp (246.08 kW) at 6,000 output rpm[3]
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.[4]
502-7B
Compressed air generator.[4]
502-8A
Turboshaft.[4]
502-8B
Turboprop, 210 hp (156.60 kW) at 37,500 compressor rpm for take-off.[4]
502-10B
Turboprop, 270 hp (201.34 kW) at 37,500 compressor rpm for take-off.[4]
502-10C
Turboshaft power unit / gas producer
502-10F
[5]
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.[3]
502-10VC
(T50-BO-8)
502-11
Compressed air generator.[4]
502-11B
502-12B
502-W
502-14
(T50-BO-10)
550-1
(T50-BO-12)

Applications

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T50 (Model 502)
GT502

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

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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.[3]

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

See also

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Related development

Related lists

References

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Notes

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  1. ^ Schenderlein, John; Clayton, Tyler (2015-12-17). "Comparison of Helicopters Turboshaft Engines" (PDF). American Institute of Aeronautics and Astronautics: 2. Retrieved 2023-06-07.
  2. ^ "Kaman Helicopters". www.airvectors.net. Retrieved 2024-05-16.
  3. ^ a b c d e Taylor, John W.R. FRHistS. ARAeS (1962). Jane's All the World's Aircraft 1962-63. London: Sampson, Low, Marston & Co Ltd.
  4. ^ a b c d e f Bridgman, Leonard (1955). Jane's all the World's Aircraft 1955-56. London: Jane's all the World's Aircraft Publishing Co. Ltd.
  5. ^ Bridgman, Leonard, ed. (1959). Jane's all the World's Aircraft 1959–60. London: Sampson Low, Marston & Co. Ltd. pp. 521–522.

Bibliography

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  • 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.
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