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Trailing Edge Film Cooling in a Transonic Cascade – Aerodynamic Experiments and Evaluation of Airfoil Loss Coefficients (European Research Project AITEB-2)

Rehder, Hans-Jürgen (2008) Trailing Edge Film Cooling in a Transonic Cascade – Aerodynamic Experiments and Evaluation of Airfoil Loss Coefficients (European Research Project AITEB-2). DLR-Interner Bericht. IB 225-2008 A 03, 133 S.

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Abstract

This report documents results from aerodynamic experiments in a linear cascade consisting of high pressure turbine blades with three different trailing edge cooling configurations. The investigations are part of Work Package 2 of the 6th European Framework Project AITEB-2 and were performed in the transonic cascade wind tunnel at DLR. Airfoil loss coefficients were evaluated from the results showing the impact of different trailing edge cooling ejection on the aerodynamic performance of the cascade.

Document Type:Monograph (DLR-Interner Bericht)
Title:Trailing Edge Film Cooling in a Transonic Cascade – Aerodynamic Experiments and Evaluation of Airfoil Loss Coefficients (European Research Project AITEB-2)
Authors:
AuthorsInstitution or Email of Authors
Rehder, Hans-JürgenUNSPECIFIED
Date:May 2008
Number of Pages:133
Status:Published
Keywords:high pressure turbine cascade, trailing edge coolant ejection, trailing edge geometries, aerodynamic experiments, airfoil loss coefficients
HGF - Research field:Energy
HGF - Program:Efficient Energy Conversion (old)
HGF - Program Themes:E VG - Combustion and Gas Turbine Technologies (old)
DLR - Research area:Energy
DLR - Program:E VG - Combustion and Gas Turbine Technologies
DLR - Research theme (Project):E - Gasturbine (old)
Location: Göttingen
Institutes and Institutions:Institute of Propulsion Technology > Turbine > Turbine Technologie
Deposited By: Stephanie Klein
Deposited On:29 May 2008
Last Modified:27 Apr 2009 14:58

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