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Bristol Siddeley BS100



The Bristol Siddeley BS.100 was a British twin-spool, vectored thrust, turbofan aero engine that first ran in 1960, the engine was designed and built Bristol Siddeley Engines Limited.
The BS.100 was similar in general arrangement to that of the company's Pegasus design, but with the addition of plenum chamber burning (PCB), to enable the projected Hawker Siddeley P.1154 VSTOL fighter design to accelerate to supersonic speed. PCB is akin to reheat, but is only applied to the bypass stream (i.e. the front nozzles), as the flow turns from fan exit to the nozzle bearing plane. Variable area front nozzles were required, to maintain consistent fan matching regardless of whether the PCB was alight.
The BS.100 was also intended for the Fokker Republic D-24.
Six had been built when the project was cancelled in early 1965.


Type: Turbofan
Dry weight:
Compressor: Two-spool axial flow
Bypass ratio: 0.9:1
Combustors: annular
Maximum thrust:
26,200 lbf (116.54 kN) PCB off
35,900 lbf (159.69 kN) short lift thrust, PCB on
Overall pressure ratio: 11.45:1
Specific fuel consumption:
0.615 lb/(hr·lbf) (62.73 kg/(kN·h)) at 19,200 lbf (85.41 kN) dry thrust
1.16 lb/(hr·lbf) (118.3 kg/(kN·h)) with PCB



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