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The Junkers Jumo 004 Aircraft Engine

Although the Junkers Jumo 004 was not the first turbojet to be designed or run it was the first turbojet to go into production, it was also the first engine used operationally (Messerschmitt Me 262), and more noteworthy, it was the Worlds first axial compressor produced as well as operated. The rapid development of the Junkers Jumo 004 was both rapid and held back at the same time due to the ravages of war.

Junkers Jumo 004 Aircraft Engine

 

Once it became clear that new weapons and technology would be required the turbojet program was speeded up, the timescale forced on the programs head, Dr Anselm Franz, to keep the design simple to avoid development time he did not have, the result was an engine which he knew only scratched the surface of what could be done if he had more time, also instead of developing new materials they had war driven shortages of even existing ones after the first eighty engines had been produced. The result was a design with great potential but not the reliability of the British turbojet engines, service life often being at little as 10 hours, rapidly throttling up being decidedly damaging to the engine.

It is of note that the Junkers Jumo 004 was started using a built in 10hp two-stroke engine mounted in the centre of the engine's air intake, it was it's self started with a pull cord by ground crew. The Jumo was also made after WW2 in the  Soviet Union as the RD-10 engine, and in Czechoslovakia by Malešice as the M-04.

Aircraft that were powered by the Junkers Jumo 004

Arado Ar 234 Heinkel He 280 Horten Ho 229
Junkers Ju 287 Messerschmitt Me 262  
     

Junkers Jumo 004B Specifications:

  • Type: Axial flow turbojet

  • Length: 3.86 m (152 in)

  • Diameter: 0.810 m (32 in)

  • Dry weight: 719 kg (1,585 lb)

  • Compressor: 8-stage axial compressor

  • Combustors: Can-type, 6

  • Turbine: Single-stage

  • Maximum thrust: 8.8 kN (1,980 lbf) at 8,700 rpm

  • Overall pressure ratio: 3.14:1

  • Specific fuel consumption: 0.139 kg/(N·hr)

  • Thrust-to-weight ratio: 1.25 (12.2 N/kg)

 

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