| 词条 | Walter HWK 109-509 | ||||||||||||||
| 释义 |
The Walter HWK 109-509 was a German liquid-fuel bipropellant rocket engine that powered the Messerschmitt Me 163 Komet and Bachem Ba 349 aircraft. It was produced by Hellmuth Walter Kommanditgesellschaft (HWK) commencing in 1943, with license production by the Heinkel firm's facilities in Jenbach, Austria. Design and developmentEarly versions of the Me 163 had been powered by an earlier design running on a "cold engine" fueled with Z-Stoff. This fuel tended to clog the jets in the combustion chamber, causing fluctuations in power and potentially explosions. Worse, however, was the fact that the engine could not be throttled, and when the aircraft leveled off after its climb to altitude it quickly accelerated to speeds that caused serious compressibility issues. The RLM demanded that a version be developed with a throttle. During this period Walter has also been working with a new fuel known as C-Stoff that gave off significant heat and was thus known as the "hot engine". C-Stoff was a mix of 30% hydrazine hydrate + 57% methanol + 13% water with a small amount of potassium-copper-cyanide. The oxidizer, known as T-Stoff, consisted of an 80%-concentration hydrogen peroxide-based formulation. The two reacted violently on contact.[2] The violent combustion process resulted in the formation of water, carbon dioxide and nitrogen, and a huge amount of heat sending out a superheated stream of steam, nitrogen and air that was drawn in through the hole in the mantle of the engine, thus providing a forward thrust of approximately 17 kN (3,820 lbf). To address the throttling issue, the new engine included turbopumps with two settings. The pumps were driven by a single turbine, powered by steam created by decomposing the T-Stoff with a wire mesh catalyst.[3] Combined with a mechanical throttle, this provided four power settings from idle to full power for climbing. In practice it was found that throttling the engine dramatically decreased its fuel economy to the point that it did not extend the endurance of the aircraft as expected. This version was put into the Me 163B in spite of this problem. The ultimate solution to the throttling problem was the B and C series of the engine. These engines used two combustion chambers, the original one (retroactively given the name Hauptofen), and a second, smaller Marschofen chamber directly beneath the main Hauptofen chamber, tuned to provide the cruise power needed for high-speed level flight, about {{convert|400|kgf}}. This chamber provided that power at peak efficiency, so it did not suffer from the problems found while throttling on the original models. The throttle on the original combustion chamber was removed, and throttling was instead provided by turning the main engine on and off. This new version dramatically improved cruise endurance, with overall flight times improving from eight to twelve minutes, a 50% improvement. It was also mechanically simpler as the turbopumps were no longer throttled. The engine was an integral design with all components of the drive, with the exception of fuel tanks, locked in a cubical frame — this frame was discarded for the 109-509C dual-chamber design. Variants
Applications
Engines on display
Specifications (509A)Data from: Jane's [8]{{rocketspecs|type=Liquid-fuelled rocket engine |length= |diameter= |weight=165.5 kg (365 lb) |compressor= |combustion= |turbine= |fueltype= T-Stoff (Hydrogen peroxide) oxidizer and C-Stoff (hydrazine hydrate/alcohol mix) fuel propellants |oilsystem= |power= |thrust=14.7 kN (3,300 lbf) |compression= |aircon= |turbinetemp= |fuelcon=8 kg/s (17.75 lb/s) at full thrust |specfuelcon= 20 lb/hr/lbf (1800 N-s/kg) |power/weight= |thrust/weight= }} See also{{aircontent|see also= |related= |similar aircraft= |lists=
|similar engines= }} ReferencesNotes1. ^1 HWK 109-509.A-1 Wkr.Nr. None - Shuttleworth Collection 2. ^Botho Stüwe, Peene Münde West, Weltbildverlag {{ISBN|3-8289-0294-4}}, 1998 page 220, German 3. ^Botho Stüwe, Peene Münde West, Weltbildverlag {{ISBN|3-8289-0294-4}}, 1998 Seite 221+222 4. ^NMUSAF page on the 109-509A 5. ^NMUSAF page on the 509A 6. ^NMUSAF page on the 509B 7. ^"RAF Museum, Cosford - HWK 109-509.C - Wkr.Nr. None - Additional History" photo showing 509C's complete Hauptofen combustion chamber - compare to NMUSAF 509B photo 8. ^Jane's 1989. p.285. Bibliography{{refbegin}}
External links{{Commons category}}
5 : Aircraft rocket engines|Rocket engines using hypergolic propellant|HWK rocket engines|Rocket engines using the gas-generator cycle|Rocket engines using hot cycle hydrogen peroxide propellant |
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