View in EDS

An Investigation of Coolant Within Serpentine Passages of a High-Pressure Axial Gas Turbine Blade.

Saved in:
Bibliographic Details
Title: An Investigation of Coolant Within Serpentine Passages of a High-Pressure Axial Gas Turbine Blade.
Authors: Nickol, Jeremy1,2 nickoljb@gmail.com, Mathison, Randall1,2 mathison.4@osu.edu, Dunn, Michael1,2 dunn.129@osu.edu, Jong Liu2,3 jong.liu@honeywell.com, Malak, Malak2,3 malak.malak@honeywell.com
Source: Journal of Turbomachinery. Sep2017, Vol. 139 Issue 9, p1-8. 8p.
Subjects: Gas turbine blades, Serpentine, Coolants
Abstract: Cooling flow behavior is investigated within the multiple serpentine passages with turbulators on the leading and trailing walls of an axial gas turbine blade operating at design-corrected conditions with accurate external flow conditions. Pressure and temperature measurements at midspan within the passages are obtained using miniature butt-welded thermocouples and miniature Kulite pressure transducers. These measurements, as well as airfoil surface pressure field data from a full computational fluid dynamics (CFD) simulation, are used as boundary conditions for a model that provides quantitative values of film-cooling blowing ratio for each film-cooling hole on the blade. The model accounts for the continuously changing cross-sectional area and shape of the channels, frictional pressure loss, convective heat transfer from the solid portion of the blade, massflow reduction as coolant bleeds out through film-cooling or impingement holes, compressibility effects, and the effects of blade rotation. The results of the model provide detailed coolant ejection information for a film-cooled rotating turbine airfoil operating at design-corrected conditions and also account for the highly variable freestream conditions on the airfoil. While these values are commonly known for simpler experimental geometries, they have previously either been unknown or estimated crudely for full-stage experiments of this nature. The better-quantified cooling parameters provide a bridge for better comparison with the wealth of film-cooling work already reported for simplified geometries. The calculation also shows the significant range in blowing ratio that can arise even among a single row of cooling holes associated with one of the turbulated passages, due to significant changes in both coolant and local freestream massfluxes. [ABSTRACT FROM AUTHOR]
Copyright of Journal of Turbomachinery is the property of American Society of Mechanical Engineers 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: 124065351
AccessLevel: 6
PubType: Academic Journal
PubTypeId: academicJournal
PreciseRelevancyScore: 0
IllustrationInfo
Items – Name: Title
  Label: Title
  Group: Ti
  Data: An Investigation of Coolant Within Serpentine Passages of a High-Pressure Axial Gas Turbine Blade.
– Name: Author
  Label: Authors
  Group: Au
  Data: <searchLink fieldCode="AR" term="%22Nickol%2C+Jeremy%22">Nickol, Jeremy</searchLink><relatesTo>1,2</relatesTo><i> nickoljb@gmail.com</i><br /><searchLink fieldCode="AR" term="%22Mathison%2C+Randall%22">Mathison, Randall</searchLink><relatesTo>1,2</relatesTo><i> mathison.4@osu.edu</i><br /><searchLink fieldCode="AR" term="%22Dunn%2C+Michael%22">Dunn, Michael</searchLink><relatesTo>1,2</relatesTo><i> dunn.129@osu.edu</i><br /><searchLink fieldCode="AR" term="%22Jong+Liu%22">Jong Liu</searchLink><relatesTo>2,3</relatesTo><i> jong.liu@honeywell.com</i><br /><searchLink fieldCode="AR" term="%22Malak%2C+Malak%22">Malak, Malak</searchLink><relatesTo>2,3</relatesTo><i> malak.malak@honeywell.com</i>
– Name: TitleSource
  Label: Source
  Group: Src
  Data: <searchLink fieldCode="JN" term="%22Journal+of+Turbomachinery%22">Journal of Turbomachinery</searchLink>. Sep2017, Vol. 139 Issue 9, p1-8. 8p.
– Name: Subject
  Label: Subjects
  Group: Su
  Data: <searchLink fieldCode="DE" term="%22Gas+turbine+blades%22">Gas turbine blades</searchLink><br /><searchLink fieldCode="DE" term="%22Serpentine%22">Serpentine</searchLink><br /><searchLink fieldCode="DE" term="%22Coolants%22">Coolants</searchLink>
– Name: Abstract
  Label: Abstract
  Group: Ab
  Data: Cooling flow behavior is investigated within the multiple serpentine passages with turbulators on the leading and trailing walls of an axial gas turbine blade operating at design-corrected conditions with accurate external flow conditions. Pressure and temperature measurements at midspan within the passages are obtained using miniature butt-welded thermocouples and miniature Kulite pressure transducers. These measurements, as well as airfoil surface pressure field data from a full computational fluid dynamics (CFD) simulation, are used as boundary conditions for a model that provides quantitative values of film-cooling blowing ratio for each film-cooling hole on the blade. The model accounts for the continuously changing cross-sectional area and shape of the channels, frictional pressure loss, convective heat transfer from the solid portion of the blade, massflow reduction as coolant bleeds out through film-cooling or impingement holes, compressibility effects, and the effects of blade rotation. The results of the model provide detailed coolant ejection information for a film-cooled rotating turbine airfoil operating at design-corrected conditions and also account for the highly variable freestream conditions on the airfoil. While these values are commonly known for simpler experimental geometries, they have previously either been unknown or estimated crudely for full-stage experiments of this nature. The better-quantified cooling parameters provide a bridge for better comparison with the wealth of film-cooling work already reported for simplified geometries. The calculation also shows the significant range in blowing ratio that can arise even among a single row of cooling holes associated with one of the turbulated passages, due to significant changes in both coolant and local freestream massfluxes. [ABSTRACT FROM AUTHOR]
– Name: AbstractSuppliedCopyright
  Label:
  Group: Ab
  Data: <i>Copyright of Journal of Turbomachinery is the property of American Society of Mechanical Engineers 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=124065351
RecordInfo BibRecord:
  BibEntity:
    Identifiers:
      – Type: doi
        Value: 10.1115/1.4036109
    Languages:
      – Code: eng
        Text: English
    PhysicalDescription:
      Pagination:
        PageCount: 8
        StartPage: 1
    Subjects:
      – SubjectFull: Gas turbine blades
        Type: general
      – SubjectFull: Serpentine
        Type: general
      – SubjectFull: Coolants
        Type: general
    Titles:
      – TitleFull: An Investigation of Coolant Within Serpentine Passages of a High-Pressure Axial Gas Turbine Blade.
        Type: main
  BibRelationships:
    HasContributorRelationships:
      – PersonEntity:
          Name:
            NameFull: Nickol, Jeremy
      – PersonEntity:
          Name:
            NameFull: Mathison, Randall
      – PersonEntity:
          Name:
            NameFull: Dunn, Michael
      – PersonEntity:
          Name:
            NameFull: Jong Liu
      – PersonEntity:
          Name:
            NameFull: Malak, Malak
    IsPartOfRelationships:
      – BibEntity:
          Dates:
            – D: 01
              M: 09
              Text: Sep2017
              Type: published
              Y: 2017
          Identifiers:
            – Type: issn-print
              Value: 0889504X
          Numbering:
            – Type: volume
              Value: 139
            – Type: issue
              Value: 9
          Titles:
            – TitleFull: Journal of Turbomachinery
              Type: main
ResultId 1