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 in limited numbers by Bristol Siddeley Engines Limited. The project was cancelled in early 1965.
|Bristol Siddeley BS.100 on display at the Fleet Air Arm Museum.|
|Type||Vectored thrust turbofan|
|Manufacturer||Bristol Siddeley Engines Limited|
|Major applications||Hawker Siddeley P.1154 (intended)|
Design and developmentEdit
Based on the 300-series Olympus, 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.
Engines on displayEdit
Data from Aircraft engines of the World 1966/67
- Type: Vectored thrust after-burning Turbofan with Plenum Chamber Burning (PCB)
- Length: 148 in (3,800 mm)
- Diameter: 60 in (1,500 mm)
- Dry weight: 4,000 lb (1,800 kg)
- Compressor: Two-spool axial flow, 3-stage LP compressor fan, with 7-stage HP compressor
- Combustors: annular with 20 spill type burner nozzles
- Turbine: HP single-stage with 2-stage LP turbines
- Fuel type: D.Eng.R.D.2494 / 2486 / 2498 / JP-1 / JP-4 / JP-5
- Oil system: Return system 50 psi (340 kPa)
- Gunston 1989, p.38.
- Wilkinson, Paul H. (1966). Aircraft engines of the World 1966/67 (21st ed.). London: Sir Isaac Pitman & Sons Ltd. p. 117.