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Improved Compressor Exit Diffuser for an Industrial Gas Turbine

Orth, U. and Ebbing, H. and Krain, H. and Weber, A. and Hoffmann, B. (2001) Improved Compressor Exit Diffuser for an Industrial Gas Turbine. In: ASME Turbo Expo 2001, pp. 1-10. ASME, New Orleans, USA, June 2001.

Full text not available from this repository.

Abstract

The aerodynamical design process used for the optimization of a centrifugal compressor stage is described. Advanced design tools for blade generation and 3D aerodynamic calculation methods were used. The manufacturing procedure and experimental verification is described.

Document Type:Conference or Workshop Item (Paper)
Additional Information: LIDO-Berichtsjahr=2001, monograph_id=2001-GT-323,
Title:Improved Compressor Exit Diffuser for an Industrial Gas Turbine
Authors:
AuthorsInstitution or Email of Authors
Orth, U.UNSPECIFIED
Ebbing, H.UNSPECIFIED
Krain, H.UNSPECIFIED
Weber, A.UNSPECIFIED
Hoffmann, B.UNSPECIFIED
Date:2001
Journal or Publication Title:ASME Turbo Expo 2001
Page Range:pp. 1-10
Editors:
EditorsEmail
The American Society of Mechanical Engineers, Atlanta, USA, UNSPECIFIED
Status:Published
Keywords:Radial Compressor, Diffuser, Gas Turbine
Event Title:ASME, New Orleans, USA, June 2001
Organizer:ASME
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 - Fan and Compressor 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 13:17

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