The BMW 109-718 was a liquid-fuelled rocket engine developed by BMW at their Bruckmühl facility, in Germany during the Second World War.
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Transcription
Development
The 109-718 (109 prefix number for the Reichsluftfahrtministerium, or RLM, designation used for all reaction-propulsion [rocket and gas turbine] aviation engine projects) was designed as an assist rocket for aircraft, for rapid takeoffs or to enable them to achieve high-speed sprints, akin to what Americans called "mixed power" postwar. It was combined with a standard BMW 003 jet engine, placed atop the rear turbine casing of the jet engine to create a new variant of it, the 003R, providing a total of 1,250 kg (2,760 lb) thrust at full power apiece; it was expected the units would be fitted in pairs. Unlike most RATO boosters,[i] the liquid-fuelled 718 rocket engine system comprising the second propulsive source of an 003R engine remained with the airframe at all times.[1]
The rocket motor had internal and external main chambers which were cooled by the nitric acid oxidiser, fed through a coiled spiral tube. The centrifugal fuel pumps (operating at 17,000rpm) delivered a mix of nitric acid oxidiser and hydrocarbon fuel at 735 psi (50.7 bar),[ii] a rate of 5.5 kg (12 lb) per 1,000 kg (2,200 lb) thrust per second. The 718's fuel pumps were driven by a power take-off from the jet engine which ran at 3,000 rpm. The complete unit weighed 80 kg (180 lb).[3]
Before war's end, a Messerschmitt Me 262C-2b Heimatschützer II (Home Defender II, one of four different planned designs of the rocket-boosted Me 262 C-series) was tested with a pair of 718s — each as a part of a pair of the BMW 003R "mixed-power" propulsion units — climbing to 9,150 m (30,020 ft) in just three minutes. The 109-718 was also tested aboard an He 162E, although records do not indicate the results of this test.[3]
The Germans hoped the rocket might eventually rely on the same fuel as jet aircraft.[1]
Only twenty 109-718 engines were completed by war's end, each taking some 100 hours to complete.[2]
Specifications
Data from The Race for Hitler's X-Planes: Britain's 1945 Mission to Capture Secret Luftwaffe Technology[4]
General characteristics
- Type: Liquid-propellant rocket
- Length:
- Diameter:
- Dry weight:
Components
- Compressor:
- Combustors: Catalyst ignited or Hypergolic combustion in a single combustion chamber
- Fuel type: Diesel fuel and red fuming nitric acid (RFNA / S-Stoff) oxidiser with injected catalyst or R-stoff / SV-stoff fuel and oxidiser[5]
Performance
- Maximum thrust: 12.2625 kN (2,756.7 lbf)
- Specific fuel consumption: 0.561 kg/kN/s (12.125 lb/lbf/s), which translates to an ISP of 181.75 (s), probably at sea level
Notes
- ^ Such as the parachute-droppable and reusable Walter HWK 109-500
- ^ Christopher (2013) calls it 50 atmospheres.[2]
Citations
- ^ a b Christopher (2013), p. 124.
- ^ a b Christopher (2013), p. 125.
- ^ a b Christopher (2013), pp. 124–125.
- ^ Christopher (2013), pp. 123–125.
- ^ Price, P.R, Flight Lieutenant. "Gas turbine development by BMW" (PDF). Combined Intelligence Objectives Sub-Committee. Retrieved 7 June 2014.
{{cite web}}: CS1 maint: multiple names: authors list (link)
Bibliography
- Christopher, John (2013). The Race for Hitler's X-Planes: Britain's 1945 Mission to Capture Secret Luftwaffe Technology. Stroud, UK: History Press. ISBN 978-0-7524-6457-2.
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This page was last edited on 24 October 2021, at 17:33