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

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

Kröger, G and Cornelius, C and 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.

Full text not available from this repository.

Abstract

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.

Document Type:Conference or Workshop Item (Speech, Paper)
Title:ROTOR CASING CONTOURING IN HIGH PRESSURE STAGES OF HEAVY DUTY GAS TURBINE COMPRESSORS WITH LARGE TIP CLEARANCE HEIGHTS
Authors:
AuthorsInstitution or Email of Authors
Kröger, GUNSPECIFIED
Cornelius, CUNSPECIFIED
Nicke, EUNSPECIFIED
Date:June 2009
Journal or Publication Title:Proceedings of ASME Turbo Expo 2009: Power for Land, Sea and Air
Status:Published
Keywords:clearance loss, casing contour, loss reduction, clearance vortex
Event Title:ASME Turbo Expo 2009: Power for Land, Sea and Air
Event Location:Orlando, USA
Event Type:international Conference
Event Dates:08.-12. Juni 2009
Organizer:ASME
HGF - Research field:Energy, Aeronautics, Space and Transport (old)
HGF - Program:Aeronautics, Efficient Energy Conversion (old)
HGF - Program Themes:L VU - Air Traffic and Environment (old), E VG - Combustion and Gas Turbine Technologies (old)
DLR - Research area:Energy, Aeronautics
DLR - Program:L VU - Air Traffic and Environment, E VG - Combustion and Gas Turbine Technologies
DLR - Research theme (Project):L - Air Traffic and Weather (old), E - Gasturbine (old)
Location: Köln-Porz
Institutes and Institutions:Institute of Propulsion Technology > Fan and Compressor
Deposited By: Georg Philipp Kröger
Deposited On:09 Mar 2010 11:32
Last Modified:09 Mar 2010 11:32

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.