Walter HWK 109-509

The Walter HWK 109-509 is a liquid rocket propulsion, which was developed during World War II by the engineering firm Hellmuth Walter at Kiel ( HWK). All top secret jet engines and rocket engines were given by the Reich Air Ministry (RLM) in the type number the inconspicuous prefix " 109 " is assigned. (see also: Junkers Jumo 004) The HWK 109-509 rocket engine was used among others in the Messerschmitt Me 163 and Bachem Ba 349 the.

The base was the test engine Walter R 1-203, which is also based on the principle of the "hot " Walter drive worked, at which combustion of highly reactive substances takes place in a combustion chamber. As fuels carbon material came (a mixture of 30 % hydrazine hydrate 57 % methanol 13 % water with residual amounts of potassium -copper cyanide) and as the oxidizer T -Stoff (80 % hydrogen peroxide and 20 % 8 -hydroxyquinoline ) were used. In the version A-1, the length of the engine 2,53 meters, the weight of 175 kg and the thrust 5-15 kN.

The engine was designed with an integral structure; all components of the drive, with the exception of the fuel tanks were fixed in a frame. Due to the decomposition of t- substance in a container filled with brownstone Zersetzertopf a hot steam -oxygen mixture that propelled the multi-flow turbo pump for the promotion of T- and C- substance was formed.

An advantage of the HWK 109-509 was the adjustability: the engine was switched off on altitude, after which the aircraft attacked in gliding and landing. Due to the high explosiveness of the fuel, there was a series of partially fatal accidents. On a Messerschmitt Me 163 reached Heini Dittmar 1941 as the first man to a speed of 1000 km / h

Types

• A- 0: Vorserienausführung, was manufactured after May 1943. The thrust of this engine could be controlled kp ( 2.9 kN) and 1,500 kgf ( 14.7 kN) of 300.
• A-1: Initial production version, was incorporated in August 1944 in the Messerschmitt Me 163 B. The thrust could be controlled from 100 kgf (1 kN) to 1600 kgf ( 15.7 kN) here.
• A-2: version for the Messerschmitt Me 163 C. This engine had next to the main combustion chamber also has a so march combustion chamber (also called march furnace called ), which provided an additional boost of 300 kgf ( 2.9 kN). If the main combustion chamber off, the rocket engine could be operated only with the march combustion chamber; so could the running and thus the flight time can be increased. The thrust of the main combustion chamber could be adjusted from 200 kgf (2 kN) to a maximum of 1700 kgf ( 16.7 kN).
• B-1: Increasing the Performance version of the A -1. Thrust between 100 kgf ( 1 kN ) and 2000 kgf ( 19.6 kN) variable. Used in the Me 163 B-1.
• C-1: uprated Based on the A-2 version. Thrust of the main jet from 400 kgf (3.9 kN ) and 2000 kgf ( 19.6 kN), the Reisedüse 400 kgf (3.9 kN)
• D-1: variant of the C-1 for use in the Bachem Ba 349 B. Designed for airdrop.