|Cutaway Bristol Hercules engine at the National Museum of Flight, East Fortune, Scotland|
|Type||Piston aircraft engine|
|National origin||United Kingdom|
|Manufacturer||Bristol Aeroplane Company|
|First run||January 1936|
|Major applications||Bristol Beaufighter
Handley Page Halifax
|Developed from||Bristol Perseus|
|Developed into||Bristol Centaurus|
The Bristol Hercules was a 14-cylinder two-row radial aircraft engine designed by Sir Roy Fedden and produced by the Bristol Engine Company starting in 1939. It was the first of their single sleeve valve (Burt-McCollum, or Argyll, type) designs to see widespread use, powering many aircraft in the mid-World War II timeframe.
Design and development
The rationale behind the single sleeve valve design was two-fold: to provide optimum intake and exhaust gas flow in a two-row radial engine, improving its volumetric efficiency; and to allow higher compression ratios, thus improving its thermal efficiency. The arrangement of the cylinders in two-row radials made it very difficult to utilise four valves per cylinder, consequently all non-sleeve valve two- and four-row radials were limited to the less efficient two-valve configuration. Also, as combustion chambers of sleeve-valve engines are uncluttered by valves, especially the hot exhaust valves, being comparatively smooth they allow engines to work with lower octane number fuels using the same compression ratio. Conversely, the same octane number fuel may be utilised while employing a higher compression ratio, or supercharger pressure, thus attaining either higher economy, or power output. The downside was the difficulty in maintaining sufficient cylinder and sleeve lubrication.
Bristol had introduced their first sleeve-valve designs in the 750 horsepower (560 kW) class Perseus and the 500 hp (370 kW) class Aquila that they intended to supply throughout the 1930s. Aircraft development in the era was so rapid that both engines quickly ended up at the low-power end of the military market and, in order to deliver larger engines, Bristol developed 14-cylinder versions of both. The Perseus evolved into the Hercules, and the Aquila into the Taurus.
The first Hercules engines were available in 1939 as the 1,290 hp (960 kW) Hercules I, soon improved to 1,375 hp (1,025 kW) in the Hercules II. The major version was the Hercules VI which delivered 1,650 hp (1,230 kW), and the late-war Hercules XVII produced 1,735 hp (1,294 kW).
The Hercules powered a number of aircraft including Bristol's own Beaufighter heavy fighter design although it was more commonly used on bombers. The Hercules also saw use in civilian designs, culminating in the 735 and 737 engines for such as the Handley Page Hastings C1 and C3 and Bristol Freighter. The design was also licensed for production in France by SNECMA. Except for the 2000 hp-range versions in the 1950s until there were lubricating oil improvements, it was considered to be one of the more reliable aircraft engines of the era.
A total of over 57,400 Hercules engines were built.
- Armstrong Whitworth Albemarle
- Avro Lancaster B.II
- Avro York C.II
- Bristol Beaufighter
- Bristol Freighter
- Bristol Superfreighter
- Breguet 890 Mercure
- CASA C-207 Azor
- Fokker T.IX
- Folland Fo.108
- Handley Page Halifax
- Handley Page Hastings
- Handley Page Hermes
- Nord Noratlas
- Northrop 8A (One Swedish 8A-1 was bought by Bristol to test the engine)
- Northrop Gamma 2L
- Saro Lerwick
- Short S.26
- Short Seaford
- Short Solent
- Short Stirling
- Vickers Valetta
- Vickers Varsity
- Vickers VC.1 Viking
- Vickers Wellesley
- Vickers Wellington
Specifications (Hercules II)
Data from Lumsden
- Type: 14-cylinder, two-row, supercharged, air-cooled radial engine
- Bore: 5.75 in (146 mm)
- Stroke: 6.5 in (165 mm)
- Displacement: 2,360 in³ (38.7 L)
- Length: 53.15 in (1,350 mm)
- Diameter: 55 in (1,397 mm)
- Dry weight: 1,929 lb (875 kg)
- Valvetrain: Gear-driven sleeve valves with five ports per sleeve — three intake and two exhaust
- Supercharger: Single-speed centrifugal type supercharger
- Fuel system: Claudel-Hobson carburettor
- Fuel type: 87 Octane petrol
- Cooling system: Air-cooled
- Reduction gear: Farman epicyclic gearing, 0.44:1
- Power output:
- 1,272 hp (949 kW) at 2,800 rpm for takeoff
- 1,356 hp (1,012 kW) at 2,750 rpm at 4,000 ft (1,220 m)
- Specific power: 0.57 hp/in³ (26.15 kW/l)
- Compression ratio: 7.0:1
- Specific fuel consumption: 0.43 lb/(hp•h) (261 g/(kW•h))
- Power-to-weight ratio: 0.7 hp/lb (1.16 kW/kg)
- Related development
- Comparable engines
- BMW 801
- Pratt & Whitney R-1830
- Pratt & Whitney R-2000
- Wright R-2600
- Fiat A.74
- Fiat A.80
- Gnome-Rhône 14N
- Mitsubishi Kinsei
- Nakajima Sakae
- Shvetsov ASh-82
- Related lists
- "Something Up Its Sleeve." Flight, 7 October 1937, p. 359.
- Gunston 1989, p.33.
- List from Lumsden 2003, some of these aircraft were used for test purposes, the Hercules not necessarily being the main powerplant
- Lumsden 2003, p.119.
- Bridgman, Leonard, ed. Jane's All The World's Aircraft 1945–1946. London: Samson Low, Marston & Company, Ltd 1946.
- Gunston, B. (1995) Classic World War II Aircraft Cutaways. Osprey. ISBN 1-85532-526-8
- Gunston, Bill. World Encyclopedia of Aero Engines. Cambridge, England. Patrick Stephens Limited, 1989. ISBN 1-85260-163-9
- Lumsden, Alec. British Piston Engines and their Aircraft. Marlborough, Wiltshire: Airlife Publishing, 2003. ISBN 1-85310-294-6.
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