In a linear cascade of low pressure turbine, LPT, blades, the position and strength of the vortices forming the endwall flows depends on the state of the inlet endwall boundary layer, i.e., whether it is laminar or turbulent. The latter will determine, amongst other effects, the location where the inlet boundary layer rolls up into a passage vortex, the amount of fluid that gets swept up by the passage vortex and the interaction with the pressure side separation bubble, de la Rosa Blanco et al. [1]. As a consequence, the mass-averaged stagnation pressure loss and therefore the design of a low-pressure turbine are influenced by the state of the inlet endwall boundary layer. The paragraph above highlights the importance of determining the state of the boundary layer along the endwalls if an understanding of the endwall flows in a LPT at realistic engine conditions is sought. The results presented in this paper are taken from hot film measurements performed on the endwalls of selected nozzle guide vanes from the fourth stage of the Affordable Near Term Low Emission, ANTLE, LPT rig. These results are compared with those from a low speed linear cascade of similar LPT blades. In the cold flow four-stage LPT rig, a transitional boundary layer has been found on the platforms upstream of the leading edge of the blades. The boundary layer is more turbulent nearer the leading edge of the blade and for higher Reynolds numbers. As for the passage, for both the cold flow four-stage rig and the low speed linear cascade, the new inlet boundary layer formed behind the pressure leg of the horseshoe vortex is a transitional boundary layer. The transition process progresses from the pressure to the suction surface of the passage in the direction of the secondary flow.
Skip Nav Destination
Close
Sign In or Register for Account
ASME Turbo Expo 2007: Power for Land, Sea, and Air
May 14–17, 2007
Montreal, Canada
Conference Sponsors:
- International Gas Turbine Institute
ISBN:
0-7918-4795-0
PROCEEDINGS PAPER
Endwall Boundary Layer Development in an Engine Representative Four-Stage Low Pressure Turbine Rig
Maria Vera,
Maria Vera
University of Cambridge, Cambridge, UK
Search for other works by this author on:
Elena de la Rosa Blanco,
Elena de la Rosa Blanco
University of Cambridge, Cambridge, UK
Search for other works by this author on:
Howard Hodson,
Howard Hodson
University of Cambridge, Cambridge, UK
Search for other works by this author on:
Raul Vazquez
Raul Vazquez
Industria de Turbopropulsores S.A., Madrid, Spain
Search for other works by this author on:
Maria Vera
University of Cambridge, Cambridge, UK
Elena de la Rosa Blanco
University of Cambridge, Cambridge, UK
Howard Hodson
University of Cambridge, Cambridge, UK
Raul Vazquez
Industria de Turbopropulsores S.A., Madrid, Spain
Paper No:
GT2007-27842, pp. 783-791; 9 pages
Published Online:
March 10, 2009
Citation
Vera, M, de la Rosa Blanco, E, Hodson, H, & Vazquez, R. "Endwall Boundary Layer Development in an Engine Representative Four-Stage Low Pressure Turbine Rig." Proceedings of the ASME Turbo Expo 2007: Power for Land, Sea, and Air. Volume 6: Turbo Expo 2007, Parts A and B. Montreal, Canada. May 14–17, 2007. pp. 783-791. ASME. https://doi.org/10.1115/GT2007-27842
Download citation file:
- Ris (Zotero)
- Reference Manager
- EasyBib
- Bookends
- Mendeley
- Papers
- EndNote
- RefWorks
- BibTex
- ProCite
- Medlars
Close
Sign In
9
Views
0
Citations
Related Proceedings Papers
Related Articles
Endwall Boundary Layer Development in an Engine Representative Four-Stage Low Pressure Turbine Rig
J. Turbomach (January,2009)
Separation Control on a Very High Lift Low Pressure Turbine Airfoil Using Pulsed Vortex Generator Jets
J. Turbomach (October,2011)
Predicting the Profile Loss of High-Lift Low Pressure Turbines
J. Turbomach (March,2012)
Related Chapters
Cavitating Structures at Inception in Turbulent Shear Flow
Proceedings of the 10th International Symposium on Cavitation (CAV2018)
Introduction
Design and Analysis of Centrifugal Compressors
Boundary Layer Analysis
Centrifugal Compressors: A Strategy for Aerodynamic Design and Analysis