A geometry generation framework for contoured endwalls

Research output: Chapter in Book/Report/Conference proceedingConference contribution

Abstract

The mainstream, or primary, flow in a gas turbine
annulus is characteristically two-dimensional over the midspan
region of the blading, where the radial flow is almost
negligible. Contrastingly, the flow in the endwall and tip
regions of the blading is highly three-dimensional,
characterised by boundary layer effects, secondary flow
features and interaction with cooling flows. Engine
designers employ geometric contouring of the endwall
region in order to reduce secondary flow effects and
subsequently minimise their contribution to aerodynamic
loss.
Such is the geometric variation of vane and blade
profiles - which has become a proprietary art form - the
specification of an effective endwall geometry is equally
unique to each blade-row. Endwall design methods, which
are often directly coupled to aerodynamic optimisers, are
widely developed to assist with the generation of contoured
surfaces. Most of these construction methods are limited to
the blade-row under investigation, while few demonstrate
the controllability required to offer a universal platform for
endwall design.
This paper presents a Geometry Generation Framework
(GGF) for the generation of contoured endwalls. The
framework employs an adaptable meshing strategy, capable
of being applied to any vane or blade, and a versatile
function-based approach to defining the endwall shape. The
flexibility of this novel approach is demonstrated by
recreating a selection of endwalls from the literature, which
were selected for their wide-range of contouring
approaches.
Original languageEnglish
Title of host publicationProceedings of the ASME Turbo Expo 2019: Turbomachinery Technical Conference and Exposition
PublisherAmerican Society of Mechanical Engineers (ASME)
Number of pages16
Publication statusAccepted/In press - 17 Jun 2019
EventASME Turbo Expo 2019 - Arizona, Phoenix, USA United States
Duration: 17 Jun 201921 Jun 2019
https://event.asme.org/Events/media/library/resources/turbo/Turbo-Expo-2019-Program.pdf

Conference

ConferenceASME Turbo Expo 2019
CountryUSA United States
CityPhoenix
Period17/06/1921/06/19
Internet address

Cite this

Wood, L., Jones, R., Pountney, O., Scobie, J., Rees, D. A. S., & Sangan, C. (Accepted/In press). A geometry generation framework for contoured endwalls. In Proceedings of the ASME Turbo Expo 2019: Turbomachinery Technical Conference and Exposition [GT2019-90446] American Society of Mechanical Engineers (ASME).

A geometry generation framework for contoured endwalls. / Wood, Liam; Jones, Robin; Pountney, Oliver; Scobie, James; Rees, D A S; Sangan, Carl.

Proceedings of the ASME Turbo Expo 2019: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers (ASME), 2019. GT2019-90446.

Research output: Chapter in Book/Report/Conference proceedingConference contribution

Wood, L, Jones, R, Pountney, O, Scobie, J, Rees, DAS & Sangan, C 2019, A geometry generation framework for contoured endwalls. in Proceedings of the ASME Turbo Expo 2019: Turbomachinery Technical Conference and Exposition., GT2019-90446, American Society of Mechanical Engineers (ASME), ASME Turbo Expo 2019, Phoenix, USA United States, 17/06/19.
Wood L, Jones R, Pountney O, Scobie J, Rees DAS, Sangan C. A geometry generation framework for contoured endwalls. In Proceedings of the ASME Turbo Expo 2019: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers (ASME). 2019. GT2019-90446
Wood, Liam ; Jones, Robin ; Pountney, Oliver ; Scobie, James ; Rees, D A S ; Sangan, Carl. / A geometry generation framework for contoured endwalls. Proceedings of the ASME Turbo Expo 2019: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers (ASME), 2019.
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AB - The mainstream, or primary, flow in a gas turbineannulus is characteristically two-dimensional over the midspanregion of the blading, where the radial flow is almostnegligible. Contrastingly, the flow in the endwall and tipregions of the blading is highly three-dimensional,characterised by boundary layer effects, secondary flowfeatures and interaction with cooling flows. Enginedesigners employ geometric contouring of the endwallregion in order to reduce secondary flow effects andsubsequently minimise their contribution to aerodynamicloss.Such is the geometric variation of vane and bladeprofiles - which has become a proprietary art form - thespecification of an effective endwall geometry is equallyunique to each blade-row. Endwall design methods, whichare often directly coupled to aerodynamic optimisers, arewidely developed to assist with the generation of contouredsurfaces. Most of these construction methods are limited tothe blade-row under investigation, while few demonstratethe controllability required to offer a universal platform forendwall design.This paper presents a Geometry Generation Framework(GGF) for the generation of contoured endwalls. Theframework employs an adaptable meshing strategy, capableof being applied to any vane or blade, and a versatilefunction-based approach to defining the endwall shape. Theflexibility of this novel approach is demonstrated byrecreating a selection of endwalls from the literature, whichwere selected for their wide-range of contouringapproaches.

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