Large Engines Combustor Demonstrator - Technology Demonstration - Investigation of First Advanced Cooling Mixing Concept
Diers, O. and Behrendt, T. and Cordes, S. and Fischer, M. and Koopman, J. and Hassa, C. (1999) Large Engines Combustor Demonstrator - Technology Demonstration - Investigation of First Advanced Cooling Mixing Concept. Project Report, DLR-Interner Bericht. 325-07-99, 52 S.
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In this experimental research a low NOx-emission rich burn quick quench lean burn pilot stage combustor for a radial staged aeroengine has been investigated. . In particular the cooling of the primary zone and the effectiveness of the mixing module is of interest. Therefore the central sector of an atmospheric rectangular five nozzle RQL combustor with effusion air cooling in primary and secondary zone and a mixing zone with two rows of holes on each side has been studied. Non-instrusive measurement methods like LDA and CARS and conventional methods like gas analysis and thermocouple measurements have been used. Velocities, temperatures and exhaust concentrations have been measured from the end of the primary zone to the defined combustor end. The results of this investigation allow to describe the progress and the performance of combustion process.
|Document Type:||Monograph (Project Report, DLR-Interner Bericht)|
|Title:||Large Engines Combustor Demonstrator - Technology Demonstration - Investigation of First Advanced Cooling Mixing Concept|
|Number of Pages:||52|
|Keywords:||Aeroengines, combustor, combustor cooling, RQL|
|HGF - Research field:||Aeronautics, Space and Transport|
|HGF - Program:||Aeronautics|
|HGF - Program Themes:||L - no assignement|
|DLR - Research area:||Aeronautics|
|DLR - Program:||L TT - Triebwerkstechnologien|
|DLR - Research theme (Project):||L - Combustion Chamber Technologies|
|Institutes and Institutions:||Institute of Propulsion Technology|
|Deposited By:||elib DLR-Beauftragter|
|Deposited On:||16 Sep 2005|
|Last Modified:||06 Jan 2010 13:08|
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