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Bristol Siddeley BS.100

From Wikipedia, the free encyclopedia
1960s British turbofan aircraft engine

BS.100
Bristol Siddeley BS.100 on display at theFleet Air Arm Museum.
TypeVectored thrustturbofan
ManufacturerBristol Siddeley Engines Limited
First run1960
Major applicationsHawker Siddeley P.1154 (intended)
Number built6

TheBristol Siddeley BS.100 is a British twin-spool,vectored thrust,turbofanaero engine that first ran in 1960. The engine was designed and built in limited numbers byBristol Siddeley Engines Limited. The project was cancelled in early 1965.

Design and development

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Based on the 300-seriesOlympus,[1] the BS.100 was similar in general arrangement to that of the company'sPegasus design, but with the addition ofplenum chamber burning (PCB), to enable the projectedHawker Siddeley P.1154 VSTOL fighter design to accelerate to supersonic speed[2] and to allow the aircraft to hover.

PCB is similar toreheat, but combustion is only applied to the bypass air (i.e. the front nozzles). PCB was quite difficult to develop since combustion had to occur on the bends between fan exit and entry to the two vectoring front nozzles and at much lower inlet pressure and temperature than a conventional afterburner. The PCB flame-holders were highly complex sheet metal fabrications which were difficult to envisage on a 2D engineering drawing. Consequently 3D models in wood had to be produced to aid development of the system.[3]

Variable area front nozzles were required. This was to be achieved by movable ramps mounted horizontally on the fuselage between the front and rear nozzles. For vertical flight and subsonic cruise, the nozzle area would be large, whereas with the PCB lit during acceleration to supersonic speed the ramps would be expanded, reducing flow to the front nozzles and diverting more flow into the core.[3]

Although PCB ran on a Pegasus 2 development engine, it was never fitted to any of the BS.100-8 engines that were built and never flew.[3]

The BS.100 was also intended for theFokker Republic D-24.[4][5]

Variants

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A range of BS.100 engines were studied in the early 1960s, but it was the BS.100-8 that was finally selected for development manufacture and was actually built.[3]

Engines on display

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A preserved Bristol Siddeley BS.100 is on public display at theFleet Air Arm Museum,RNAS Yeovilton.

Specifications (BS.100-8)

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Data fromPegasus:The Heart Of The Harrier.[3]

General characteristics

  • Type: Vectored thrust after-burningturbofan with Plenum Chamber Burning (PCB)
  • Length: 107 in (2,700 mm) fan entry to exhaust cone truncation
  • Diameter: 52 in (1,300 mm) fan
  • Dry weight:

Components

  • Compressor: Two-spool axial flow, 4-stage LP compressor fan, with 7-stage HP compressor
  • Turbine: HP cooled single-stage with 2-stage uncooled LP turbines
  • Fuel type: Kerosene

Performance

  • Maximumthrust:
    • 26,200 lbf (116.5 kN) PCB off
    • 33,140 lbf (147.4 kN) normal lift thrust, PCB on, 20 second rating
    • 35,170 lbf (156.4 kN) short lift thrust, PCB on, 140 second rating
  • Overall pressure ratio: 11.45:1
  • Bypass ratio: 0.934:1
  • Air mass flow: 490 lb/s (220 kg/s)
  • Turbine inlet temperature: 1,447K short lift
  • Specific fuel consumption: 0.773 lb/(lbf.h)21.9g/(kN.s) PCB off

See also

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Related development

Comparable engines

Related lists

References

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Notes

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  1. ^Flightglobal archive - 1962
  2. ^Gunston 1989, p.38.
  3. ^abcdeDow 2009, ch. 6
  4. ^Flightglobal archive
  5. ^Flightglobal archive Fokker-Republic D-24

Bibliography

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  • Gunston, Bill.World Encyclopedia of Aero Engines. Cambridge, England. Patrick Stephens Limited, 1989.ISBN 1-85260-163-9
  • Dow, Andrew.Pegasus - The heart of the Harrier. Barnsley, South Yorkshire. Pen and Sword, 2009.ISBN 1-84884-042-X

External links

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