Walter HWK 109-509

HWK 109-509
HWK 109-509A on display at the Luftwaffenmuseum, Berlin-Gatow, Germany
Type	Rocket engine
Manufacturer	Hellmuth Walter Kommanditgesellschaft
First run	1943
Major applications	Messerschmitt Me 163 Bachem Ba 349

The HWK 109-509 was a German liquid-fuel bipropellant rocket engine that powered the Messerschmitt Me 163 and Bachem Ba 349 aircraft. It was produced by Hellmuth Walter Kommanditgesellschaft (HWK) commencing in 1943.

Design and development

Early 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 a hydrogen peroxide-based formulation. The two reacted violently on contact. 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 (3,800 dbf).

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. 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, and a second tuned to provide the cruise power needed for high-speed level flight, about 400 kilograms-force (3,900 N; 880 lbf). 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

• A-0: Pre-production model, manufactured from May 1943. The thrust of this engine was regulated between 300 kp (2.9 kN) and 1500 kp (14.7 kN (3,300 lbf)).
• A-1: The first series production engine was used in the Messerschmitt Me 163 B from August 1944. The thrust here was adjustable between 100 kp (1 kN) and 1600 kp (15.7 kN (3,500 lbf)).
• A-2: Version for the Messerschmitt Me 163B-1a. Weighing only 100 kg (220 lb) complete, this engine consisted of two main assemblies, the roughly-cubical shape framed forward assembly comprising the turbine housing, the fuel pumps geared to the turbine shaft, the control box, a pressure-reducing valve and the electric starter motor, with the aft assembly made up of the combustion chamber, connected to the fore unit by a cylindrical "thrust-tube" containing pipes which carried fuel to the combustion chamber's individual injector jets. The thrust was adjustable between 200 kp (2 kN (450 lbf)) and a maximum of 1700 kp (16.7 kN (3,800 lbf)).

The HWK 109-509B dual-chamber version, on display at the NMUSAF

• B-1: Increased performance version of the A-1. This engine had a second, "cruising" combustion chamber, nicknamed the Marschofen, just below the main combustion chamber (nicknamed the Hauptofen for the twin-chamber configuration), with an additional thrust of 300 kp (2.9 kN (650 lbf)). This auxiliary chamber proved necessary due to the actual T-Stoff oxidizer consumption of the main unit, at nearly 5 kg/s, exceeding estimates by 100%. Thrust from main chamber adjustable between 100 kp (1 kN (220 lbf)) and 2000 kp (19.6 kN (4,400 lbf)). One surviving example — stated as the third prototype example — at the National Museum of the U.S. Air Force, near its own preserved A-series example.
• C-1: Dual-chamber motor like the B-series, based on the uprated version of the A-2, but also discarding the open-structure cubical frame for lighter weight. The main combustion chamber gave between 400 kp (3.9 kN (880 lbf)) and 2000 kp (19.6 kN (4,400 lbf)), the Marschofen auxiliary chamber 400 kp (3.9 kN (880 lbf)). To be used in the Me 263 (Ju 248).One surviving example on museum display at the Royal Air Force Museum Cosford.
• D-1: Variant of the C-1 for use in the improved B-series airframes of the Bachem Ba 349 Natter. Engine designed to be recovered by parachute, along with the entire rear section with empennage.
• S-2 A completely revised lightened version for use as a permanently-installed booster rocket on the Messerschmitt Me 262 Heimatschützer IV home defence interceptor.
• 'HWK RII-211 - Company designation for prototype engines of the 109-509A-2 series

Applications

• Arado Ar E.381
• Bachem Ba 349
• DFS 228
• Focke-Wulf Volksjäger 2
• Messerschmitt Me 163
• Messerschmitt Me 262C, in Heimatschützer prototype evaluation designs.

Engines on display

• National Museum of the United States Air Force (both single-chamber -A and twin-chamber -B versions)
• National Museum of Flight
• Luftwaffenmuseum der Bundeswehr
• Shuttleworth Collection
• Ballarat Aviation Museum

Specifications (109-509A)

Data from: Jane's

General characteristics

• Type: Liquid-fuelled rocket engine
• Length:
• Diameter:
• Dry weight: 165.5 kg (365 lb)
• Fuel: T-Stoff (Hydrogen peroxide) oxidizer and C-Stoff (hydrazine hydrate/alcohol mix) fuel propellants

Components

• Pumps:

Performance

• Thrust: 14.7 kN (3,300 lbf)
• Burn time:
• Thrust specific fuel consumption: 20lb/hr/lbf (1800 N.s/kg)

See also

Related lists

• List of aircraft engines
• List of aircraft engines of Germany during World War II

References

Bibliography

• Jane's Fighting Aircraft of World War II. London. Studio Editions Ltd, 1989. ISBN 0-517-67964-7

External links

• The Hellmuth Walter Rocket Engine
• The Hellmuth Walter Rocket Engine sitepage, on the NMUSAF-preserved 109-509B rocket motor
• Walter 109-509B rocket motor photo-page
• The NMUSAF page on the 509B
• The Hellmuth Walter Rocket Engine sitepage, on the RAF Museum/Cosford-preserved 109-509C rocket motor and photos of the preserved UK-housed 509C rocket motor