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词条 Bristol Theseus
释义

  1. Applications

  2. Variants

  3. Specifications (Theseus Th.21)

  4. See also

  5. References

     Notes  Bibliography 

  6. External links

{{Use dmy dates|date=December 2016}}{{Use British English|date=December 2016}}
name=Theseusimage=bristol.theseus.arp.750pix.jpgcaption=Preserved Bristol Theseus

}}{{Infobox Aircraft Engine

type=Turbopropmanufacturer=Bristol Siddeley1945}}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The engine was soon superseded by the Proteus design with more power, and the only extended use of the engine was in two Handley Page Hermes 5 development aircraft.[1]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

  • Avro Theseus Lincoln[4]
  • Handley Page Hermes 5

Variants

Theseus Series TH.11

Variant without heat exchanger

Theseus Series TH.21

Variant with heat exchanger

Specifications (Theseus Th.21)

{{jetspecs
|ref=Aircraft Engines of the world 1946[5]
|type=Mixed compressor turboprop with heat exchanger
|length={{convert|106|in|m|abbr=on|2}}
|diameter={{convert|49|in|m|abbr=on|2}}
|weight={{convert|2,310|lb|kg|abbr=on}}
|compressor=8-stage axial + 1-stage centrifugal compressors feeding the combustion chambers through a heat exchanger
|combustion=8 x stainless steel can combustion chambers
|turbine=2-stage axial + 1-stage axial free turbine driving the propeller
|fueltype=Kerosene (R.D.E. / F / KER)
|oilsystem=pressure feed to bearings, dry sump, 40 S.U. secs (13 cSt) (Intavia 620) grade oil
|power={{convert|2,800|hp|kW|abbr=on}} equivalent at 8,200 rpm at sea level [6]
|thrust=
|compression=3:1
|bypass=
|aircon=
|turbinetemp=
|fuelcon={{convert|272|impgal/h|l/h|abbr=on}}
|specfuelcon=0.5 lb/equiv. hp/h ( kg/equiv. kW/h) {{clarify|date=December 2016}}
|power/weight=1.02 equiv. hp/lb (1.677 equiv. kW/kg) {{clarify|date=December 2016}}
|thrust/weight=
  • Maximum flight rating: {{convert|1,500|hp|kW|abbr=on}} equivalent at 8,200 rpm at {{convert|20,000|ft|m|abbr=on}}

}}

See also

  • List of aircraft engines

References

Notes

1. ^Gunston 1989, p.34.
2. ^{{cite journal | title=Theseus Air Testing - First Bristol Airscrew Turbines Fly in a Lincoln : Some Features Discussed | journal= Flight | page= 270| date= 27 March 1947 |url=http://www.flightglobal.com/pdfarchive/view/1947/1947%20-%200444.html}}
3. ^http://www.flightglobal.com/pdfarchive/view/1947/1947%20-%200602.html
4. ^Test bed only
5. ^{{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}}
6. ^{{convert|2,200|hp|kW|abbr=on}} plus {{convert|825|lbf|kN|abbr=on|2}} residual thrust

Bibliography

{{refbegin}}
  • Gunston, Bill. World Encyclopedia of Aero Engines. Cambridge, England. Patrick Stephens Limited, 1989. {{ISBN|1-85260-163-9}}
{{refend}}

External links

{{Commons category|Bristol Theseus}}
  • "Bristol Theseus I" a 1945 Flight article
  • Development of the turboprop Flight 30 November 1950
{{BristolAeroengines}}

3 : Turboprop engines 1940–1949|Bristol aircraft engines|Mixed-compressor gas turbines

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