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Fan Shaped And Cylindrical Holes Studied in a Vane Film Cooling Test Rig
Siemens Industrial Turbomachinery AB, Finspong, Sweden.
Siemens Industrial Turbomachinery AB, Finspong, Sweden.
Siemens Industrial Turbomachinery AB, Finspong, Sweden.
Florida Center for Advanced Aero-Propulsion Florida State University, College of Engineering Tallahassee, USA.
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2010 (English)In: Proceedings of the Asme Turbo Expo 2010, Vol 4, Pts a and B, 2010, 1777-1784 p.Conference paper, Published paper (Refereed)
Abstract [en]

In order to optimize the vane film cooling and thereby increase the efficiency of a gas turbine, different film cooling configurations were experimentally investigated. Dynamic similarity was obtained regarding main flow Reynolds number, airfoil pressure coefficient, adiabatic wall temperature and film cooling ejection ratio. The maximum reached Mach number was 0.52. The geometry of the test section, consisting of one vane and two flow paths, was modified in order to meet the dimensionless pressure coefficient distribution around the airfoil experienced by a full stage airfoil. This would ascertain that scaled but engine realistic pressure gradients would be achieved in the rig test.

During the test, the cold airfoil was suddenly imposed to a hot main stream and the evaluation of both the film cooling effectiveness and the heat transfer coefficient distribution on the visiable surface could be done at one single test using timeresolved temperature measurements obtained through IR thermography. A high resolution MWIR camera was used together with a silicon viewing window. The post-processing allowed for corrections regarding emissions and determination of the desired parameters on the vane surface.

Results, heat transfer coefficients and film cooling effectiveness, for fan shaped and cylindrical film cooling holes configurations are compared. The results show clear benefit of using shaped holes over cylindrical ditto, especially on the suction side where near hole film effectiveness is enhanced by approximately 25%, but the results also show that this benefit diminishes to nothing in the suction side trailing edge region.

The local heat transfer coefficients are generally lower for the shaped hole configurations. Contrary to the film effectiveness the shaped holes configurations show lower heat transfer coefficients also at the suction side trailing edge region, making use of the shaped hole configurations superior to cylindrical ones as the heat flux to the surface is reduced.

Numerical predictions using a boundary layer code, TEXSTAN, and CFD, for a smooth wall configuration corresponds well with the measured results.

Place, publisher, year, edition, pages
2010. 1777-1784 p.
National Category
Engineering and Technology
Identifiers
URN: urn:nbn:se:liu:diva-91707DOI: 10.1115/GT2010-23308ISI: 000290693500155ISBN: 978-0-7918-4399-4 (print)ISBN: 978-0-7918-3872-3 (print)OAI: oai:DiVA.org:liu-91707DiVA: diva2:618749
Conference
ASME Turbo Expo 2010: Power for Land, Sea, and Air, GT 2010; Glasgow; United Kingdom
Available from: 2013-04-30 Created: 2013-04-30 Last updated: 2016-03-14Bibliographically approved
In thesis
1. CFD Simulations for Film Cooling: Reduced Models at Engine Like Conditions
Open this publication in new window or tab >>CFD Simulations for Film Cooling: Reduced Models at Engine Like Conditions
2013 (English)Licentiate thesis, comprehensive summary (Other academic)
Abstract [en]

In gas turbines some parts are exposed to combustion gases with temperatures well above the melting temperature of the material. Therefore, various cooling techniques are utilized in order to protect the parts exposed to these hot gases. One such technique, film cooling, is a common and well established way to protect the exposed parts. Film cooling involves the ejection of cold air on the surface of the parts that are to be protected, thus creating a film of colder air between the surface and the hot gases.

Computational Fluid Dynamics (CFD) is a way of calculating fluid flow, and can be used to calculate the effectiveness of a cooling film in film cooling applications. CFD is demanding in terms of computer power, especially when advanced methods are to be used. Even the simpler methods, such as Reynolds Average Navier-Stokes (RANS), can be quite demanding, time and computer power-wise, and require resources not always available. Finding ways of limiting the needed computer power is therefore of large interest.

The aim of this thesis is to reduce the computational time of film cooling CFD-simulations, by using reduced models. To achieve this, simulations has been conducted and compared to experiments. The investigated setup is of an enginelike equipment, where a guide vane is investigated for heat transfer coefficient and film effectiveness. The geometry in the experimental setup is constructed in such a way as to give the same pressure distribution around the guide vane as can be seen in a real gas turbine, although at lower temperatures than those in the real turbine. The CFD-simulations conducted on the test rig includes RANS-simulations using the realizable k- and the SST k-! turbulence models.

The reduced model contains only the central part of the vane. The walls of the test rig is replaced with periodic boundary conditions. This narrow model gives good agreement with the full model for heat transfer coefficient. Due to the large computational cost required to conduct simulations with cooling on the full model no comparison were made between the cooled narrow and cooled full model.

To further reduce the size of the computational domain, two additional models were investigated. The first one involves a reduction of the full domain to only include the section being studied, in this case the suction side of the guide vane.

This infers a reduction of the mesh size to less than ten percent of the size of what a mesh of the cooled full domain would be. The next step to reduce the size of the model and mesh is to make a narrow version of the already shortened model. The results for these two models show that they perform adequately to each other and (in the cases where a comparison is possible), to the full domain.

Place, publisher, year, edition, pages
Linköping: Linköping University Electronic Press, 2013. 44 p.
Series
Linköping Studies in Science and Technology. Thesis, ISSN 0280-7971 ; 1593
National Category
Engineering and Technology
Identifiers
urn:nbn:se:liu:diva-91716 (URN)
Presentation
2013-05-31, Sal C3, C-huset, Campus Valla, Linköpings universitet, Linköping, 10:15 (English)
Opponent
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Available from: 2013-04-30 Created: 2013-04-30 Last updated: 2017-12-14Bibliographically approved

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Bradley, AndreasKarlsson, MattsWren, Joakim

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