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

Film-Cooled Turbine Endwall in a Transonic Flow Field. Part I - Aerodynamic Measurements

Kost, F. and Nicklas, M. (2001) Film-Cooled Turbine Endwall in a Transonic Flow Field. Part I - Aerodynamic Measurements. In: ASME TURBO EXPO 2001. ASME TURBO EXPO 2001, New Orleans, USA, 4.-7. Juni 2001, New Orleans, USA.

Full text not available from this repository.

Abstract

Thermodynamic and aerodynamic measurements were carried out in a linear turbine ascade ith transonic flow field. Heat transfer and adiabatic film-cooling effectiveness resulting from the interaction of the flow field and the ejected coolant at the endwall were measured and will be discussed in two parts. The investigations were performed in the Windtunnel for Straight Cascades (EGG) at DLR, Goettingen. The film-cooled NGV endwall was operated at representative nondimensional engine conditions regarding Mach and Reynolds number (Ma_2=1.0, Re_2=850,000). Part I of the investigations discusses the aerodynamic measurements. Detailed aerodynamic measurements were carried out in the vicinity of a turbine stator endwall using conventional pressure measurements and a Laser-2-Focus (L2F) device. The L2F served as a velocimeter measuring 2D-velocity vectors and turbulence quantities and as a tool to determine the concentration of coolant ejected through a slot and through holes at the endwall. Pressure distribution measurements provided information on the endwall pressure field and its variation with coolant flow rate. Pressure probe measurements delivered cascade performance data. Oil flow visualization and Laser velocimetry gave a picture of the near endwall flow field and its interference with the coolant. A strikingly strong interaction of coolant air and secondary flow field could be identified. The measurement of coolant concentration downstream of the ejection locations provided a detailed picture of the coolant flow convection and its mixing with the main flow. The relative coolant concentration in the flow field is directly comparable to the adiabatic film-cooling effectiveness measured by thermal methods at the wall.

Document Type:Conference or Workshop Item (Paper)
Additional Information: LIDO-Berichtsjahr=2001,
Title:Film-Cooled Turbine Endwall in a Transonic Flow Field. Part I - Aerodynamic Measurements
Authors:
AuthorsInstitution or Email of Authors
Kost, F.UNSPECIFIED
Nicklas, M.UNSPECIFIED
Date:2001
Journal or Publication Title:ASME TURBO EXPO 2001
Editors:
EditorsEmail
ASME, UNSPECIFIED
Series Name:2001-GT-0145
Status:Published
Keywords:Transonic flow, Turbine flow, Turbine platform, Endwall, Secondary Flow, Laser velocimetry, L2F, Coolant flow, Aerodynamic measurements, Film cooling effectiveness
Event Title:ASME TURBO EXPO 2001, New Orleans, USA, 4.-7. Juni 2001
Event Location:New Orleans, USA
Event Type:international Conference
Organizer:ASME
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: Köln-Porz
Institutes and Institutions:Institute of Propulsion Technology
Deposited By: elib DLR-Beauftragter
Deposited On:16 Sep 2005
Last Modified:06 Jan 2010 13:13

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.