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ROTOR CASING CONTOURING IN HIGH PRESSURE STAGES OF HEAVY DUTY GAS TURBINE COMPRESSORS WITH LARGE TIP CLEARANCE HEIGHTS

Kröger, G und Cornelius, C und Nicke, E (2009) ROTOR CASING CONTOURING IN HIGH PRESSURE STAGES OF HEAVY DUTY GAS TURBINE COMPRESSORS WITH LARGE TIP CLEARANCE HEIGHTS. In: Proceedings of ASME Turbo Expo 2009: Power for Land, Sea and Air. ASME Turbo Expo 2009: Power for Land, Sea and Air, 08.-12. Juni 2009, Orlando, USA.

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Kurzfassung

Clearance leakage losses of axial compressor rotors and stators have a major impact on the overall compressor performance. The clearance heights in the last stages (high pressure stages) of a gas turbine compressor are very large in comparison to the low pressure stages due to mechanical constraints and small blade heights. The reduction of clearance leakage losses in a high pressure stage still holds an important potential for the overall performance improvement at design point conditions. In the following work, a method for tip clearance loss reduction by circumferential casing contouring above a high pressure stage rotor with a constant clearance height is presented. The subsonic compressor blade provides Siemens HPA-Family [1, 2, 3] airfoils. Starting over with a 3DOptimization of the mentioned rotor casing the work additionally refers to the aerodynamic effects and the off design performance of the optimized geometry. It has been found that an optimized casing and blade tip contour lead to a smaller overall clearance mass flow and lower pressure loss coefficient of the clearance flow so that the endwall blockage is reduced and the stage performance is improved by about 0.35% at design point conditions. Furthermore it was found that the performance improvement drops with increasing exit pressure to about 0.1% close to stall conditions. At lower exit pressure values the optimized geometry provides an additional performance improvement in comparison to the baseline configuration.

Dokumentart:Konferenzbeitrag (Vortrag, Paper)
Titel:ROTOR CASING CONTOURING IN HIGH PRESSURE STAGES OF HEAVY DUTY GAS TURBINE COMPRESSORS WITH LARGE TIP CLEARANCE HEIGHTS
Autoren:
AutorenInstitution oder E-Mail-Adresse der Autoren
Kröger, GNICHT SPEZIFIZIERT
Cornelius, CNICHT SPEZIFIZIERT
Nicke, ENICHT SPEZIFIZIERT
Datum:Juni 2009
Erschienen in:Proceedings of ASME Turbo Expo 2009: Power for Land, Sea and Air
Status:veröffentlicht
Stichwörter:clearance loss, casing contour, loss reduction, clearance vortex
Veranstaltungstitel:ASME Turbo Expo 2009: Power for Land, Sea and Air
Veranstaltungsort:Orlando, USA
Veranstaltungsart:internationale Konferenz
Veranstaltungsdatum:08.-12. Juni 2009
Veranstalter :ASME
HGF - Forschungsbereich:Energie, Verkehr und Weltraum (alt)
HGF - Programm:Luftfahrt, Rationelle Energieumwandlung (alt)
HGF - Programmthema:L VU - Luftverkehr und Umwelt (alt), E VG - Verbrennungs- und Gasturbinentechnik (alt)
DLR - Schwerpunkt:Energie, Luftfahrt
DLR - Forschungsgebiet:L VU - Luftverkehr und Umwelt, E VG - Verbrennungs- und Gasturbinentechnik
DLR - Teilgebiet (Projekt, Vorhaben):L - Luftverkehr und Wetter (alt), E - Gasturbine (alt)
Standort: Köln-Porz
Institute & Einrichtungen:Institut für Antriebstechnik > Fan- und Verdichter
Hinterlegt von: Georg Philipp Kröger
Hinterlegt am:09 Mär 2010 11:32
Letzte Änderung:09 Mär 2010 11:32

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