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CFD analysis of first stage nozzle cooling optimization in power station gas turbine

Computational Fluid Dynamics analysis on First Stage Nozzle in full scale multi-stage power station gas turbine has been carried out. The main aim is to investigate the turbine thermal performance when cooling rate decreases at certain level. All calculations were executed using commercial CFD code,...

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Main Authors: Hasini H., Fadhil S.S.A., Jaafar M.N.M., Malek N.A., Ujir M.H.
Other Authors: 6507435998
Format: Article
Published: Penerbit UTM Press 2023
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spelling my.uniten.dspace-222462023-05-29T13:59:49Z CFD analysis of first stage nozzle cooling optimization in power station gas turbine Hasini H. Fadhil S.S.A. Jaafar M.N.M. Malek N.A. Ujir M.H. 6507435998 55812738800 57216608088 36994735300 36633279200 Computational Fluid Dynamics analysis on First Stage Nozzle in full scale multi-stage power station gas turbine has been carried out. The main aim is to investigate the turbine thermal performance when cooling rate decreases at certain level. All calculations were executed using commercial CFD code, ANSYS FLUENT which is able to accurately predict the flow and conjugate heat transfer problem as demonstrated in this investigation. The modelling of gas turbine nozzle is assisted by geometric cloud data obtained from 3D scan. Preliminary calculation shows that at the given worst case scenario for, the maximum thermal stress experienced by the component is within the maximum yield strength of the nozzle material. However, the safety margin between the predicted stress and maximum allowable stress is very small. � 2015 Penerbit UTM Press. All rights reserved. Final 2023-05-29T05:59:49Z 2023-05-29T05:59:49Z 2015 Article 10.11113/jt.v76.5540 2-s2.0-84942119114 https://www.scopus.com/inward/record.uri?eid=2-s2.0-84942119114&doi=10.11113%2fjt.v76.5540&partnerID=40&md5=e201fb4ed4a91fde98208de4744155c8 https://irepository.uniten.edu.my/handle/123456789/22246 76 5 73 78 Penerbit UTM Press Scopus
institution Universiti Tenaga Nasional
building UNITEN Library
collection Institutional Repository
continent Asia
country Malaysia
content_provider Universiti Tenaga Nasional
content_source UNITEN Institutional Repository
url_provider http://dspace.uniten.edu.my/
description Computational Fluid Dynamics analysis on First Stage Nozzle in full scale multi-stage power station gas turbine has been carried out. The main aim is to investigate the turbine thermal performance when cooling rate decreases at certain level. All calculations were executed using commercial CFD code, ANSYS FLUENT which is able to accurately predict the flow and conjugate heat transfer problem as demonstrated in this investigation. The modelling of gas turbine nozzle is assisted by geometric cloud data obtained from 3D scan. Preliminary calculation shows that at the given worst case scenario for, the maximum thermal stress experienced by the component is within the maximum yield strength of the nozzle material. However, the safety margin between the predicted stress and maximum allowable stress is very small. � 2015 Penerbit UTM Press. All rights reserved.
author2 6507435998
author_facet 6507435998
Hasini H.
Fadhil S.S.A.
Jaafar M.N.M.
Malek N.A.
Ujir M.H.
format Article
author Hasini H.
Fadhil S.S.A.
Jaafar M.N.M.
Malek N.A.
Ujir M.H.
spellingShingle Hasini H.
Fadhil S.S.A.
Jaafar M.N.M.
Malek N.A.
Ujir M.H.
CFD analysis of first stage nozzle cooling optimization in power station gas turbine
author_sort Hasini H.
title CFD analysis of first stage nozzle cooling optimization in power station gas turbine
title_short CFD analysis of first stage nozzle cooling optimization in power station gas turbine
title_full CFD analysis of first stage nozzle cooling optimization in power station gas turbine
title_fullStr CFD analysis of first stage nozzle cooling optimization in power station gas turbine
title_full_unstemmed CFD analysis of first stage nozzle cooling optimization in power station gas turbine
title_sort cfd analysis of first stage nozzle cooling optimization in power station gas turbine
publisher Penerbit UTM Press
publishDate 2023
_version_ 1806423265991720960
score 13.211869

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