elib
DLR-Header
DLR-Logo -> http://www.dlr.de
DLR Portal Home | Impressum | Kontakt | English
Schriftgröße: [-] Text [+]

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

Kost, F. und 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.

Dieses Archiv kann nicht den gesamten Text zur Verfügung stellen.

Kurzfassung

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.

Dokumentart:Konferenzbeitrag (Paper)
Zusätzliche Informationen: LIDO-Berichtsjahr=2001,
Titel:Film-Cooled Turbine Endwall in a Transonic Flow Field. Part I - Aerodynamic Measurements
Autoren:
AutorenInstitution oder E-Mail-Adresse der Autoren
Kost, F.NICHT SPEZIFIZIERT
Nicklas, M.NICHT SPEZIFIZIERT
Datum:2001
Erschienen in:ASME TURBO EXPO 2001
Herausgeber:
HerausgeberInstitution und/oder E-Mail-Adresse der Herausgeber
ASME, NICHT SPEZIFIZIERT
Name der Reihe:2001-GT-0145
Status:veröffentlicht
Stichwörter:Transonic flow, Turbine flow, Turbine platform, Endwall, Secondary Flow, Laser velocimetry, L2F, Coolant flow, Aerodynamic measurements, Film cooling effectiveness
Veranstaltungstitel:ASME TURBO EXPO 2001, New Orleans, USA, 4.-7. Juni 2001
Veranstaltungsort:New Orleans, USA
Veranstaltungsart:internationale Konferenz
Veranstalter :ASME
HGF - Forschungsbereich:Energie
HGF - Programm:Rationelle Energieumwandlung (alt)
HGF - Programmthema:E VG - Verbrennungs- und Gasturbinentechnik (alt)
DLR - Schwerpunkt:Energie
DLR - Forschungsgebiet:E VG - Verbrennungs- und Gasturbinentechnik
DLR - Teilgebiet (Projekt, Vorhaben):E - Gasturbine (alt)
Standort: Köln-Porz
Institute & Einrichtungen:Institut für Antriebstechnik
Hinterlegt von: elib DLR-Beauftragter
Hinterlegt am:16 Sep 2005
Letzte Änderung:06 Jan 2010 13:13

Nur für Mitarbeiter des Archivs: Kontrollseite des Eintrags

Blättern
Suchen
Hilfe & Kontakt
Informationen
electronic library verwendet EPrints 3.3.12
Copyright © 2008-2013 Deutsches Zentrum für Luft- und Raumfahrt (DLR). Alle Rechte vorbehalten.