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Boeing T50

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T50
Type

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This page is a soft redirect. Turboprop #REDIRECTmw:Help:Magic words#Other
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National origin

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Manufacturer

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Major applications

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The Boeing T50 (company designation Model 502) was a small turboshaft engine produced by Boeing. 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.

Variants

T50-BO-4
Script error: No such module "convert". at 6,000 output rpm, military rating turboprop.[1]
T50-BO-6
T50-BO-8
Script error: No such module "convert". at 5,950 output rpm, revised reduction gear ratio, fuelsystem and other changes.[1]
T50-BO-8A
T50-BO-10
Script error: No such module "convert". at 6,000 output rpm[1]
T50-BO-12
502-2E
Turboprop, Script error: No such module "convert". at 2,900 output rpm max. continuous at sea level.[2]
502-7B
Compressed air generator.[2]
502-8A
Turboshaft.[2]
502-8B
Turboprop, Script error: No such module "convert". at 37,500 compressor rpm for take-off.[2]
502-10B
Turboprop, Script error: No such module "convert". at 37,500 compressor rpm for take-off.[2]
502-10C
502-10V
(T50-BO-4)
502-10VB
Script error: No such module "convert". at 3,000 output rpm, variant of -10V / T50-B0-4 with revised reduction gear ratio.[1]
502-10VC
(T50-BO-8)
502-11
Compressed air generator.[2]
502-12B
502-W
502-14
(T50-BO-10)
550-1
(T50-BO-12)

Applications

T50 (Model 502)
GT502

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

File:QH-50 05-1526 DD-692.jpg
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.[1]

General characteristics

  • Type: Turboshaft
  • Length: Script error: No such module "convert".
  • Diameter: Script error: No such module "convert".
  • Dry weight: Script error: No such module "convert".

Components

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

Performance

  • Maximum power output: Script error: No such module "convert". military rating at 6,000 output shaft rpm
  • Overall pressure ratio: 4.35:1
  • Air mass flow: Script error: No such module "convert"./sec
  • Turbine inlet temperature: Jet pipe Temperature: Script error: No such module "convert".
  • Specific fuel consumption: 0.87 lb/hp-hr (0.532 kg/kW-hr)
  • Power-to-weight ratio: 1.535 hp/lb (2.523 kW/kg)

See also

Related lists

Notes

  1. ^ 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. 
  2. ^ 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. 

References

  • 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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External links

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