elib
DLR-Header
DLR-Logo -> http://www.dlr.de
DLR Portal Home | Imprint | Contact | Deutsch
Fontsize: [-] Text [+]

The Influence of Cooling Air Ejection on Flow Development and Heat Transfer in a Rotating Leading Edge Coolant Duct of a Film-Cooled Turbine Blade

Elfert, M. (2001) The Influence of Cooling Air Ejection on Flow Development and Heat Transfer in a Rotating Leading Edge Coolant Duct of a Film-Cooled Turbine Blade. In: Part B - Heat Transfer and Cooling in Propulsion and Power Systems, pp. 1-12. Nato, RTO (Research and Technology Organization, Paris, Frankreich. AVT Spring Meeting and Panel Business Week, Part B - Heat Transfer and Cooling in Propulsion and Power Systems Symposium on Advanced Flow Management, May 7-11, 2001, Loen, Norway.

Full text not available from this repository.

Abstract

With increasing turbine inlet temperature, the cooling of gas turbine components exposed to the hot gas flow will be of great importance. The improvement of the efficiency demands higher performance from the blade cooling systems with minimized coolant flow rates to cope with the increase in heat load as well as to meet the obligatory safety requirements. This calls for very accurate knowledge of the gas and coolant side flow and heat transfer, which both affect the blade temperature field, in order to obtain an efficient cooling design. This paper provides information about rotational effects on fluid motion and heat transfer within a rotating coolant duct of circular cross section with bleeding of cooling air through a row of film cooling holes for the purpose of film cooling of the hot gas side of the blade. Experimental data were obtained from a model mounted to the rotating duct facility at DLR. Flow development were measured by a non-intrusive optical Laser velocimeter. Wall temperature distributions around the duct wall and the generated heat were measured to provide data for local heat transfer analysis. The direction of bleeding is varied against the direction of rotation to study its effect on the development of secondary vortex structures which are generally caused within the flow by the rotational forces. Depending on the direction of bleeding, secondary vortex motion as well as heat transfer variation around the duct circumference are enhanced with pressure side ejection or weakened with suction side ejection.

Document Type:Conference or Workshop Item (Paper)
Additional Information: LIDO-Berichtsjahr=2002, monograph_id=Paper 16B,
Title:The Influence of Cooling Air Ejection on Flow Development and Heat Transfer in a Rotating Leading Edge Coolant Duct of a Film-Cooled Turbine Blade
Authors:
AuthorsInstitution or Email of Authors
Elfert, M.UNSPECIFIED
Date:2001
Journal or Publication Title:Part B - Heat Transfer and Cooling in Propulsion and Power Systems
Page Range:pp. 1-12
Editors:
EditorsEmail
RTO, UNSPECIFIED
Publisher:Nato, RTO (Research and Technology Organization, Paris, Frankreich
Status:Published
Keywords:Film Cooling, Turbine Blade, Rotation, Vortex, Bleeding
Event Title:AVT Spring Meeting and Panel Business Week, Part B - Heat Transfer and Cooling in Propulsion and Power Systems Symposium on Advanced Flow Management, May 7-11, 2001, Loen, Norway
Organizer:Research and Technology Organization (RTO)
HGF - Research field:Aeronautics, Space and Transport (old)
HGF - Program:Efficient Energy Conversion (old)
HGF - Program Themes:E VG - Combustion and Gas Turbine Technologies (old)
DLR - Research area:Aeronautics
DLR - Program:E VG - Combustion and Gas Turbine Technologies
DLR - Research theme (Project):E - Gasturbine (old)
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 13:19

Repository Staff Only: item control page

Browse
Search
Help & Contact
Informationen
electronic library is running on EPrints 3.3.12
Copyright © 2008-2012 German Aerospace Center (DLR). All rights reserved.