View in EDS

Turbine vane film cooling: Heat transfer evaluation using high-order discontinuous Galerkin RANS computations.

Saved in:
Bibliographic Details
Title: Turbine vane film cooling: Heat transfer evaluation using high-order discontinuous Galerkin RANS computations.
Authors: Bassi, F.1, Fontaneto, F.2, Franchina, N.1 nicoletta.franchina@unibg.it, Ghidoni, A.3, Savini, M.1
Source: International Journal of Heat & Fluid Flow. Oct2016 Part B, Vol. 61, p610-625. 16p.
Subjects: Turbines, Cooling, Galerkin methods, Finite element method, Turbine blades, Fluid flow
Abstract: A high-order accurate CFD solver, based on the Discontinuous Galerkin (DG) finite element method, is here employed to compute the heat transfer, with and without film coolant injection, around a turbine vane extensively tested in a wind tunnel. The numerical solution makes also use of a high-order polynomial representation of the airfoil curved boundary in order to minimize the numerical sources of error, leaving possibly only those related to the physical model adopted. The objective of the work is therefore twofold: on the one hand to provide a detailed investigation, often beyond the reach of the experiments, of the complex flow field arising in a film-cooled gas turbine cascade, on the other hand to ascertain the limits of the Reynolds-averaged Navier-Stokes (RANS) approach and its associated turbulence model when using high-order accurate methods. The DG formulation is briefly reviewed, as well as the experimental apparatus and the measuring technique, and then the code is applied to the computation of various test cases characterized by different reference Reynolds and Mach numbers. Two-dimensional results (up to seventh-order accurate) obtained both with the high- and low-Reynolds version of the k - ω model employed are presented. Reasonably good agreement between experimental and numerical results is obtained, even though the outcomes are far from being completely satisfactory especially for flow regimes in the low Reynolds number range. This is due to the lack of suitable modeling of the laminar-turbulent transition process taking place around the blade leading edge. Such a complex phenomenon is out of reach of the modeling capabilities of the high-Re k - ω model, while can be roughly mimicked by the low-Re version of the model, which is able to provide a delayed onset of the turbulence quantities along the blade surface. Third-order accurate computation of the three-dimensional turbine vane are also presented in this work and compared with available measurements to investigate the relevant fluid flow phenomena occurring and to discuss significant issues related to an accurate prediction of the turbine wall heat transfer. [ABSTRACT FROM AUTHOR]
Copyright of International Journal of Heat & Fluid Flow is the property of Elsevier B.V. and its content may not be copied or emailed to multiple sites without the copyright holder's express written permission. Additionally, content may not be used with any artificial intelligence tools or machine learning technologies. However, users may print, download, or email articles for individual use. This abstract may be abridged. No warranty is given about the accuracy of the copy. Users should refer to the original published version of the material for the full abstract. (Copyright applies to all Abstracts.)
Database: Engineering Source
FullText Text:
  Availability: 0
Header DbId: egs
DbLabel: Engineering Source
An: 120146200
AccessLevel: 6
PubType: Academic Journal
PubTypeId: academicJournal
PreciseRelevancyScore: 0
IllustrationInfo
Items – Name: Title
  Label: Title
  Group: Ti
  Data: Turbine vane film cooling: Heat transfer evaluation using high-order discontinuous Galerkin RANS computations.
– Name: Author
  Label: Authors
  Group: Au
  Data: <searchLink fieldCode="AR" term="%22Bassi%2C+F%2E%22">Bassi, F.</searchLink><relatesTo>1</relatesTo><br /><searchLink fieldCode="AR" term="%22Fontaneto%2C+F%2E%22">Fontaneto, F.</searchLink><relatesTo>2</relatesTo><br /><searchLink fieldCode="AR" term="%22Franchina%2C+N%2E%22">Franchina, N.</searchLink><relatesTo>1</relatesTo><i> nicoletta.franchina@unibg.it</i><br /><searchLink fieldCode="AR" term="%22Ghidoni%2C+A%2E%22">Ghidoni, A.</searchLink><relatesTo>3</relatesTo><br /><searchLink fieldCode="AR" term="%22Savini%2C+M%2E%22">Savini, M.</searchLink><relatesTo>1</relatesTo>
– Name: TitleSource
  Label: Source
  Group: Src
  Data: <searchLink fieldCode="JN" term="%22International+Journal+of+Heat+%26+Fluid+Flow%22">International Journal of Heat & Fluid Flow</searchLink>. Oct2016 Part B, Vol. 61, p610-625. 16p.
– Name: Subject
  Label: Subjects
  Group: Su
  Data: <searchLink fieldCode="DE" term="%22Turbines%22">Turbines</searchLink><br /><searchLink fieldCode="DE" term="%22Cooling%22">Cooling</searchLink><br /><searchLink fieldCode="DE" term="%22Galerkin+methods%22">Galerkin methods</searchLink><br /><searchLink fieldCode="DE" term="%22Finite+element+method%22">Finite element method</searchLink><br /><searchLink fieldCode="DE" term="%22Turbine+blades%22">Turbine blades</searchLink><br /><searchLink fieldCode="DE" term="%22Fluid+flow%22">Fluid flow</searchLink>
– Name: Abstract
  Label: Abstract
  Group: Ab
  Data: A high-order accurate CFD solver, based on the Discontinuous Galerkin (DG) finite element method, is here employed to compute the heat transfer, with and without film coolant injection, around a turbine vane extensively tested in a wind tunnel. The numerical solution makes also use of a high-order polynomial representation of the airfoil curved boundary in order to minimize the numerical sources of error, leaving possibly only those related to the physical model adopted. The objective of the work is therefore twofold: on the one hand to provide a detailed investigation, often beyond the reach of the experiments, of the complex flow field arising in a film-cooled gas turbine cascade, on the other hand to ascertain the limits of the Reynolds-averaged Navier-Stokes (RANS) approach and its associated turbulence model when using high-order accurate methods. The DG formulation is briefly reviewed, as well as the experimental apparatus and the measuring technique, and then the code is applied to the computation of various test cases characterized by different reference Reynolds and Mach numbers. Two-dimensional results (up to seventh-order accurate) obtained both with the high- and low-Reynolds version of the k - ω model employed are presented. Reasonably good agreement between experimental and numerical results is obtained, even though the outcomes are far from being completely satisfactory especially for flow regimes in the low Reynolds number range. This is due to the lack of suitable modeling of the laminar-turbulent transition process taking place around the blade leading edge. Such a complex phenomenon is out of reach of the modeling capabilities of the high-Re k - ω model, while can be roughly mimicked by the low-Re version of the model, which is able to provide a delayed onset of the turbulence quantities along the blade surface. Third-order accurate computation of the three-dimensional turbine vane are also presented in this work and compared with available measurements to investigate the relevant fluid flow phenomena occurring and to discuss significant issues related to an accurate prediction of the turbine wall heat transfer. [ABSTRACT FROM AUTHOR]
– Name: AbstractSuppliedCopyright
  Label:
  Group: Ab
  Data: <i>Copyright of International Journal of Heat & Fluid Flow is the property of Elsevier B.V. and its content may not be copied or emailed to multiple sites without the copyright holder's express written permission. Additionally, content may not be used with any artificial intelligence tools or machine learning technologies. However, users may print, download, or email articles for individual use. This abstract may be abridged. No warranty is given about the accuracy of the copy. Users should refer to the original published version of the material for the full abstract.</i> (Copyright applies to all Abstracts.)
PLink https://search.ebscohost.com/login.aspx?direct=true&site=eds-live&db=egs&AN=120146200
RecordInfo BibRecord:
  BibEntity:
    Identifiers:
      – Type: doi
        Value: 10.1016/j.ijheatfluidflow.2016.07.007
    Languages:
      – Code: eng
        Text: English
    PhysicalDescription:
      Pagination:
        PageCount: 16
        StartPage: 610
    Subjects:
      – SubjectFull: Turbines
        Type: general
      – SubjectFull: Cooling
        Type: general
      – SubjectFull: Galerkin methods
        Type: general
      – SubjectFull: Finite element method
        Type: general
      – SubjectFull: Turbine blades
        Type: general
      – SubjectFull: Fluid flow
        Type: general
    Titles:
      – TitleFull: Turbine vane film cooling: Heat transfer evaluation using high-order discontinuous Galerkin RANS computations.
        Type: main
  BibRelationships:
    HasContributorRelationships:
      – PersonEntity:
          Name:
            NameFull: Bassi, F.
      – PersonEntity:
          Name:
            NameFull: Fontaneto, F.
      – PersonEntity:
          Name:
            NameFull: Franchina, N.
      – PersonEntity:
          Name:
            NameFull: Ghidoni, A.
      – PersonEntity:
          Name:
            NameFull: Savini, M.
    IsPartOfRelationships:
      – BibEntity:
          Dates:
            – D: 02
              M: 10
              Text: Oct2016 Part B
              Type: published
              Y: 2016
          Identifiers:
            – Type: issn-print
              Value: 0142727X
          Numbering:
            – Type: volume
              Value: 61
          Titles:
            – TitleFull: International Journal of Heat & Fluid Flow
              Type: main
ResultId 1