Large Engines Combustor Demonstrator - Technology Demonstration - Investigation of Second Advanced Cooling Mixing Concept
Diers, O. and Koopman, J. and Hassa, C. (2000) Large Engines Combustor Demonstrator - Technology Demonstration - Investigation of Second Advanced Cooling Mixing Concept. Project Report, DLR-Interner Bericht. 325-03-2000, 64 S.
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This report describes the experimental results of the investigation of an atmospheric rich burn quick quench lean burn pilot stage for a radially staged aeroengine combustor. The central sector of a rectangular five nozzle RQL combustor with impingement cooling in the primary and film cooling in the secondary zone has been studied. In this combustion concept secondary air is brought into the combustor through one row of secondary air inlet holes on each side of the liner, enveloped by primary zone cooling air. Velocities, temperatures and exhaust concentrations have been measured from the end of the primary zone to the defined combustor end. The results allow to describe the suitability of the combustion process.
|Document Type:||Monograph (Project Report, DLR-Interner Bericht)|
|Title:||Large Engines Combustor Demonstrator - Technology Demonstration - Investigation of Second Advanced Cooling Mixing Concept|
|Number of Pages:||64|
|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 13:10|
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