Bristol Theseus

The Theseus was the Bristol Aeroplane Company's first attempt at a gas-turbine engine design, a turboprop that delivered just over 2,000 hp (1,500 kW). A novel feature was the use of a heat exchanger to transfer waste heat from the exhaust to the compressor exit. The engine was soon superseded by the Proteus design with more power, and the only extended use of the engine was in two Handley Page Hermes 5 development aircraft.[1]

Theseus
Preserved Bristol Theseus
Type Turboprop
Manufacturer Bristol Siddeley
First run 18 July 1945
Major applications Handley Page Hermes

Following 156 hours of ground runs and the receipt of a test certificate from the Ministry of Supply on 28 January 1947, two Theseus engines were fitted in the outer positions of a four-engined Avro Lincoln for air tests.[2] After ground and taxying test the Lincoln first flew on 17 February 1947.[2]

As well as being one of the first engines to feature a free propeller turbine, the Theseus was the first turboprop in the world to pass a type test, doing so in January 1947.[3]

Applications

Bristol Theseus on public display

East Midlands Aeropark Castle Donington.

Variants
Theseus Series TH.11
Variant without heat exchanger
Theseus Series TH.21
Variant with heat exchanger
Theseus 502

Specifications (Theseus Th.21)

Data from Aircraft Engines of the world 1946[5]

General characteristics

  • Type: Mixed compressor turboprop with heat exchanger
  • Length: 106 in (2.69 m)
  • Diameter: 49 in (1.24 m)
  • Dry weight: 2,310 lb (1,050 kg)

Components

  • Compressor: 8-stage axial + 1-stage centrifugal compressors feeding the combustion chambers through a heat exchanger
  • Combustors: 8 x stainless steel can combustion chambers
  • Turbine: 2-stage axial + 1-stage axial free turbine driving the propeller
  • Fuel type: Kerosene (R.D.E. / F / KER)
  • Oil system: pressure feed to bearings, dry sump, 40 S.U. secs (13 cSt) (Intavia 620) grade oil

Performance

  • Maximum power output: 2,800 hp (2,100 kW) equivalent at 8,200 rpm at sea level [6]
  • Overall pressure ratio: 3:1
  • Fuel consumption: 272 imp gal/h (1,240 l/h)
  • Specific fuel consumption: 0.5 lb/equiv. hp/h ( kg/equiv. kW/h)
  • Thrust-to-weight ratio:
  • Maximum flight rating: 1,500 hp (1,100 kW) equivalent at 8,200 rpm at 20,000 ft (6,100 m)
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See also

References

Notes
  1. Gunston 1989, p.34.
  2. "Theseus Air Testing - First Bristol Airscrew Turbines Fly in a Lincoln : Some Features Discussed". Flight: 270. 27 March 1947.
  3. http://www.flightglobal.com/pdfarchive/view/1947/1947%20-%200602.html
  4. Test bed only
  5. Wilkinson, Paul H. (1946). Aircraft Engines of the world 1946. London: Sir Isaac Pitman & Sons. pp. 284–285.
  6. 2,200 hp (1,600 kW) plus 825 lbf (3.67 kN) residual thrust

Bibliography
  • Gunston, Bill. World Encyclopedia of Aero Engines. Cambridge, England. Patrick Stephens Limited, 1989. ISBN 1-85260-163-9
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