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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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Abstract

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)
Additional Information: LIDO-Berichtsjahr=2000,
Title:Large Engines Combustor Demonstrator - Technology Demonstration - Investigation of Second Advanced Cooling Mixing Concept
Authors:
AuthorsInstitution or Email of Authors
Diers, O.UNSPECIFIED
Koopman, J.UNSPECIFIED
Hassa, C.UNSPECIFIED
Date:2000
Number of Pages:64
Status:Published
Keywords:Aeroengines, combustor, combustor cooling, RQL
HGF - Research field:Aeronautics, Space and Transport (old)
HGF - Program:Aeronautics
HGF - Program Themes:other
DLR - Research area:Aeronautics
DLR - Program:L TT - Triebwerkstechnologien
DLR - Research theme (Project):L - Combustion Chamber Technologies
Location: Köln-Porz
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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