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Design and Performance Investigations of a Transonic Turbine Rotor Cascade

Kondareddypally Nanjundappa, Abhishek und Rehder, Hans-Jürgen (2008) Design and Performance Investigations of a Transonic Turbine Rotor Cascade. DLR-Interner Bericht. 225-2008 A 01, 49 S.

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Kurzfassung

The main focus of the thesis work is to investigate the performance and suitable design improvements of a transonic turbine rotor cascade. The Bezier parametric curve is used to represent the geometric blade definition. The semi-analytical algorithm is developed to determine the control points of the Bezier curve which can reproduce the initial shape accurately with a minimum number of control points. The numerical flow field simulations are carried out using a cascade analysis code - MISES. The computational method - MISES has quite a good agreement with the experimental results. Two fold intuitive design change were employed namely curvature change along the rear part of suction side and reduction of trailing edge radius for the VKI-1 profile. Flow field simulations were carried out for four different profiles. The losses for profile-1, with trailing edge radius same as VKI-1 are reduced to about 2.5% for supersonic Mach number and shows a slight increase for Mach numbers 0.8 and 1.0. For profiles with reduced trailing edge radii, the losses are reduced around 3% for Mach numbers 0.8 and 1.0 and around 1% for Mach number 1.2 between the final and initial profile.

Dokumentart:Berichtsreihe (DLR-Interner Bericht)
Titel:Design and Performance Investigations of a Transonic Turbine Rotor Cascade
Autoren:
AutorenInstitution oder E-Mail-AdresseAutoren-ORCID
Kondareddypally Nanjundappa, AbhishekNICHT SPEZIFIZIERTNICHT SPEZIFIZIERT
Rehder, Hans-JürgenNICHT SPEZIFIZIERTNICHT SPEZIFIZIERT
Datum:Februar 2008
In Open Access:Nein
In SCOPUS:Nein
In ISI Web of Science:Nein
Seitenanzahl:49
Status:veröffentlicht
Stichwörter:transonic turbine cascade, Bezier curve representation, numerical simulation, MISES code, performance investigation, trailing edge thickness, suction side curvature
HGF - Forschungsbereich:keine Zuordnung
HGF - Programm:Luftfahrt
HGF - Programmthema:Antriebe (alt)
DLR - Schwerpunkt:Luftfahrt
DLR - Forschungsgebiet:L ER - Antriebsforschung
DLR - Teilgebiet (Projekt, Vorhaben):L - Turbinentechnologien (alt)
Standort: Göttingen
Institute & Einrichtungen:Institut für Antriebstechnik > Turbine > Turbinentechnologie
Hinterlegt von: Klein, Stephanie
Hinterlegt am:20 Feb 2008
Letzte Änderung:27 Apr 2009 14:46

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