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Rolls-Royce Clyde

RB.39 Clyde
Rolls-Royce Clyde on display at the Rolls-Royce Heritage Trust, Derby
Type Turboprop
Manufacturer Rolls-Royce Limited
First run 5 August 1945[1]
Number built 9[2]

The Rolls-Royce RB.39 Clyde was Rolls-Royce's first purpose-designed turboprop engine and the first turboprop engine to pass its civil and military type-tests.[2][3]

As with subsequent Rolls-Royce gas turbines, it was named after a river, the River Clyde.

Design and development

The Clyde used a two-shaft design, with an axial compressor based on that of the Metrovick F.2[4][5] for the low-pressure section, and a single-sided centrifugal compressor scaled up from the Merlin 46 supercharger[6] as the high-pressure stage, both mounted on the HP shaft and driven by a single stage HP turbine. A single stage power turbine drove the front mounted propeller reduction gearbox via the concentric LP shaft. A fairly novel feature of this compact gearbox was the power output to contra-rotating propellers.[7]

The Clyde was a long engine with the axial LP compressor in front of what was, in effect, a scaled-down Derwent engine. Accessories were grouped around the axial compressor which conveniently narrowed towards the rear. Cooling for turbines and turbine bearings came from a small impeller on the main shaft as well as air taken from the axial and centrifugal compressors. Testing of the development engines exceeded expectations with the engine soon being rated at 4,030 eshp.[5][1] During testing potentially destructive vibrations were found originating in the straight-cut spur gears in the reduction gearbox.[1]

The engine was selected as the main engine of the Westland Wyvern TF Mk.2 strike aircraft.[2] However, despite the promising performance of the test engines Ernest Hives felt that pure-jets such as the Avon were the future and the Clyde programme was terminated, forcing Westland to use the less than satisfactory Armstrong Siddeley Python on the production Wyverns.[2] and so Rolls-Royce's first production turboprop would be the Dart.

Engines on display

A part sectioned example is on display at the Rolls-Royce Heritage Trust, (Derby).

Specifications (Clyde)

Side view with sectioned combustion chamber

Data from Turbojet History and Development 1930-1960 vol.1.[1]

General characteristics

  • Type: Two-Shaft Turboprop
  • Length: 121.2 in (3,080 mm)
  • Diameter: 46.8 in (1,190 mm)
  • Dry weight: 2,800 lb (1,300 kg) (dry)

Components

  • Compressor: LP - 9 stage axial, HP - Single centrifugal stage
  • Combustors: Eleven can-type combustion chambers
  • Turbine:' HP - single stage axial, Power - single stage axial
  • Fuel type: Kerosene (jet fuel grade)e
  • Oil system: Pressure spray scavenge system

Performance

See also

Related lists

References

Notes

  1. ^ a b c d Kay, Anthony L. (2007). "14". Turbojet History and Development 1930-1960 vol.1 (1st ed.). Marlborough: The Crowood Press. pp. 105–118. ISBN 978-1-86126-912-6.
  2. ^ a b c d Gunston, Bill (2006). World Encyclopedia of Aero Engines (5th ed.). Stroud: Sutton Publishing. pp. 194–195. ISBN 0-7509-4479-X.
  3. ^ Flight 1954, p. 582.
  4. ^ McKenzie, A. (2001). Axial Compressor Development at Rolls-Royce Derby, 1946–1962. Rolls-Royce Heritage Trust. pp. 10, 23. ISBN 978-1-872922-42-3. Technical Series Nº11.
  5. ^ a b "World Encyclopedia of Aero Engines – 5th edition" by Bill Gunston, Sutton Publishing, 2006, P.195
  6. ^ Feilden, G. B. R. (2005). "Lionel Haworth. 4 August 1912 — 12 April 2000". Biographical Memoirs of Fellows of the Royal Society. 51: 195–220. doi:10.1098/rsbm.2005.0013. S2CID 60786773.
  7. ^ "Not much of an Engineer" by Sir Stanley Hooker, Airlife Publishing Ltd, 1984, P.227

Bibliography

Quelle: https://en.wikipedia.org/wiki/Rolls-Royce_Clyde