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contributor authorBeaux, Jean-Hugues
contributor authorGirardeau, Julian
contributor authorKhelladi, Sofiane
contributor authorDeligant, Michael
contributor authorPerilhon, Christelle
date accessioned2024-12-24T18:54:16Z
date available2024-12-24T18:54:16Z
date copyright6/18/2024 12:00:00 AM
date issued2024
identifier issn0742-4795
identifier othergtp_146_10_101016.pdf
identifier urihttp://yetl.yabesh.ir/yetl1/handle/yetl/4302955
description abstractIn gas turbines, the stator wells play a key role in the efficiency of the turbomachine. The research for performance gains requires a good understanding and an accurate modeling of the flows and heat transfers occurring in these areas. Within the framework of the European program main annulus gas path interaction (MAGPI) WP1, a two-stage axial turbine test rig provided an experimental database used to validate the computational fluid dynamics (CFD) models. The aim of this study is to setup a numerical methodology using the CFD solver ANSYSFluent to accurately predict the conjugate heat transfer in the stator well area. The validation of the methodology relies on thorough comparison of the results with the MAGPI WP1 experimental temperature/pressure measurements. A geometry with axial cooling injection through lock plate slot was chosen. A Reynolds-averaged Navier–Stokes (RANS) three-dimensional sectorized CFD model of the turbine with conjugate heat transfer was used. It includes main gas path, cavities with labyrinths, disks rotor, the casing, and the nozzle guide vanes (NGV). Mixing planes are placed between the static and rotating frames. Different influences (mesh, turbulence model, thermal boundary conditions, radial labyrinths clearances) were studied and compared with experimental data. As a baseline, the first calculations were performed with a cooling flowrate chosen so that hot gas ingresses from the main stream into the stator well cavity. Good agreements between predicted and measured temperatures/pressures were observed, especially in the vicinity of the stator well. Discrepancies were spotted at the first rotor hub endwall and at the upstream wheelspace and will be discussed. Two other cooling configurations were conducted, one with cooling air exiting from the disk rim cavity to the main gas path and the other with the lowest cooling flowrate and so the highest ingress. Finally, the turbine performance under nonadiabatic conditions has been evaluated with an appropriate efficiency definition.
publisherThe American Society of Mechanical Engineers (ASME)
titleNumerical Investigations of Flows and Heat Transfer in Turbine Disk Cavities
typeJournal Paper
journal volume146
journal issue10
journal titleJournal of Engineering for Gas Turbines and Power
identifier doi10.1115/1.4065632
journal fristpage101016-1
journal lastpage101016-16
page16
treeJournal of Engineering for Gas Turbines and Power:;2024:;volume( 146 ):;issue: 010
contenttypeFulltext


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