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High Pressure Test Rig 1 (HBK1)



HBK 1 Header

The test facility HBK1 was built to investigate aeronautical gas turbine burners in original size under realistic operation conditions. The realism extends also to the use of combustion chambers that are designed to be as close as possible to the original design. Thus, the HBK1 is operated with singles sector as well as with multisector combustors. Beside the geometrical similarity, the split of primary, secondary and mixing air is analogue to original design. To investigate the reacting flow field in all regions and zones with non-intrusive laser measurement techniques, the combustors have optical access from all sides. Due to the possibility to control all air and fuel mass flows, as well as the pressure individually and independently from each other, a large range of operating conditions can be reached, including off-design points. New technical innovations to reduce the pollution by air traffic can be investigated in the TRL4-environment of HBK1 after only very short preparation times. This is made possible by the use of in house fabricated, modular designed combustion chambers, built with Selective Laser Melting (SLM):
 

 Laser-optical investigation of a lean burn combustor (OCORE2)
zum Bild Laser-optical investigation of a lean burn combustor (OCORE2)

GENERAL INFORMATION

  • Site: Cologne-Porz, Institute of Propulsion Technology
  • In service since: 2008


TECHNICAL DATA

  • Static Pressure 20 bar
  • Air preheat temperature 900 K
  • Air mass flow 2,5-4,5 kg/s
  • Variable air and temperature split
  • Single Sector combustors
  • Multisector combustors
  • Full optical access in all combustion zones  
  • Operation with SLM manufactured combustors


FIELD OF APPLICATION

  • Investigation and characterisation of combustion systems for gas turbines and aeronautical systems:
  • Fuel placement, atomisation, vaporisation, dispersion
  • Pilot/Main burner-interaction,  flow field, stabilisation, heat release
  • Pilot burner performance, load range, soot production
  • Mixing of secondary and mixing air
  • Burner-burner interaction
  • Investigation of combustor outlet parameter  (=turbine inlet)
  • Combustion efficiency
  • Emission of pollutants
  • Thermoacoustic stability


COOPERATIONS

  • Rolls-Royce Deutschland Ltd & Co KG

Contact
Olaf Diers
German Aerospace Center

Institute of Propulsion Technology
, Combustor
Köln

Tel.: +49 2203 601-2625

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