Bristol Theseus: Difference between revisions
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|ref=<ref name=Wilkinson>{{cite book|last=Wilkinson|first=Paul H.|title=Aircraft Engines of the world 1946|year=1946|publisher=Sir Isaac Pitman & Sons|location=London|pages=284–285}}</ref> |
|ref=Aircraft Engines of the world 1946<ref name=Wilkinson>{{cite book|last=Wilkinson|first=Paul H.|title=Aircraft Engines of the world 1946|year=1946|publisher=Sir Isaac Pitman & Sons|location=London|pages=284–285}}</ref> |
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|type=Mixed compressor [[turboprop]] with heat exchanger |
|type=Mixed compressor [[turboprop]] with heat exchanger |
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|length={{convert|106|in|mm|abbr=on|1}} |
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Revision as of 20:08, 11 September 2017
| Theseus | |
|---|---|
| |
| Preserved Bristol Theseus | |
| Type | Turboprop |
| Manufacturer | Bristol Siddeley |
| First run | 18 July Template:Avyear |
| Major applications | Handley Page Hermes |
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 The engine was soon superseded by the Proteus design with more power, and the only extended use of the engine was in two Handley Page Hermes 5 development aircraft.[1]
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
Variants
- Theseus Series TH.11
- Variant without heat exchanger
- Theseus Series TH.21
- Variant with heat exchanger
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 (2,692.4 mm)
- Diameter: 49 in (1,244.6 mm)
- Dry weight: 2,310 lb (1,047.8 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 (2,087.96 kW) equivalent at 8,200 rpm at sea level (2,200 hp (1,640.54 kW) + 825 lbf (3.67 kN) residual thrust)
- Overall pressure ratio: 3:1
- Fuel consumption: 272 imp gal (1,236.5 L) /h
- Specific fuel consumption: 0.5 lb/equiv. hp/h ( kg/equiv. kW/h) [clarification needed]
- Thrust-to-weight ratio:
- Maximum flight rating: 1,500 hp (1,118.55 kW) equivalent at 8,200 rpm at 20,000 ft (6,096 m)
- Power-to-weight ratio: 1.02 equiv. hp/lb (1.677 equiv. kW/kg) [clarification needed]
See also
References
Notes
- ^ Gunston 1989, p.34.
- ^ a b "Theseus Air Testing - First Bristol Airscrew Turbines Fly in a Lincoln : Some Features Discussed". Flight: 270. 27 March 1947.
- ^ http://www.flightglobal.com/pdfarchive/view/1947/1947%20-%200602.html
- ^ Test bed only
- ^ Wilkinson, Paul H. (1946). Aircraft Engines of the world 1946. London: Sir Isaac Pitman & Sons. pp. 284–285.
Bibliography
- Gunston, Bill. World Encyclopedia of Aero Engines. Cambridge, England. Patrick Stephens Limited, 1989. ISBN 1-85260-163-9
External links
- "Bristol Theseus I" a 1945 Flight article
- Flight magazine - Theseus article 1950