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Time-Resolved Heat Transfer and Surface Pressure Measurements for a Fully Cooled Transonic Turbine Stage.

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Title: Time-Resolved Heat Transfer and Surface Pressure Measurements for a Fully Cooled Transonic Turbine Stage.
Authors: Nickol, Jeremy B.1 nickol.10@osu.edu, Mathison, Randall M.1 mathison.4@osu.edu, Malak, Malak F.2 malak.malak@honeyweil.com, Rana, Rajiv2, Liu, Jong S.2 jong.liu@honeywell.com
Source: Journal of Turbomachinery. Sep2015, Vol. 137 Issue 9, p091009-1-091009-11. 11p.
Subjects: Gas turbines, Heat transfer, Heat flux, Thermal insulation, Computational fluid dynamics
Abstract: The flow field in axial gas turbines is driven by strong unsteady interactions between stationary and moving components. While time-averaged measurements can highlight many important flow features, developing a deeper understanding of the complicated flows present in high-speed turbomachinery requires time-accurate measurements that capture this unsteady behavior. Toward this end, time-accurate measurements are presented for a fully cooled transonic high-pressure turbine stage operating at designcorrected conditions. The turbine is run in a short-duration blowdown facility with uniform, radial, and hot streak vane-inlet temperature profiles as well as various amounts of cooling flow. High-frequency response surface pressure and heat-flux instrumentation installed in the rotating blade row, stator vane row, and stationary outer shroud provide detailed measurements of the flow behavior for this stage. Previous papers have reported the time-averaged results from this experiment, but this paper focuses on the strong unsteady phenomena that are observed. Heat-flux measurements from double-sided heatflux gauges (HFGs) cover three spanwise locations on the blade pressure and suction surfaces. In addition, there are two instrumented blades with the cooling holes blocked to isolate the effect of just blade cooling. The stage can be run with the vane and blade cooling flow either on or off. High-frequency pressure measurements provide a picture of the unsteady aerodynamics on the vane and blade airfoil surfaces, as well as inside the serpentine coolant supply passages of the blade. A time-accurate computational fluid dynamics (CFD) simulation is also run to predict the blade swface pressure and heatflux, and comparisons between prediction and measurement are given. It is found that unsteady variations in heat-flux and pressure are stronger at low to midspan and weaker at high span, likely due to the impact of secondary flows such as the tip leakage flow. Away from the tip, it is seen that the unsteady fluctuations in pressure and heat-flux are mostly in phase with each other on the suction side, but there is some deviation on the pressure side. The flow field is ultimately shown to be highly three-dimensional, as the movement of high heat transfer regions can be traced in both the chord and spanwise directions. These measurements provide a unique picture of the unsteady flow physics of a rotating turbine, and efforts to better understand and model these time-varying flows have the potential to change the way we think about even the time-averaged flow characteristics. [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
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Header DbId: egs
DbLabel: Engineering Source
An: 110908572
AccessLevel: 6
PubType: Academic Journal
PubTypeId: academicJournal
PreciseRelevancyScore: 0
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  Label: Title
  Group: Ti
  Data: Time-Resolved Heat Transfer and Surface Pressure Measurements for a Fully Cooled Transonic Turbine Stage.
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  Data: <searchLink fieldCode="AR" term="%22Nickol%2C+Jeremy+B%2E%22">Nickol, Jeremy B.</searchLink><relatesTo>1</relatesTo><i> nickol.10@osu.edu</i><br /><searchLink fieldCode="AR" term="%22Mathison%2C+Randall+M%2E%22">Mathison, Randall M.</searchLink><relatesTo>1</relatesTo><i> mathison.4@osu.edu</i><br /><searchLink fieldCode="AR" term="%22Malak%2C+Malak+F%2E%22">Malak, Malak F.</searchLink><relatesTo>2</relatesTo><i> malak.malak@honeyweil.com</i><br /><searchLink fieldCode="AR" term="%22Rana%2C+Rajiv%22">Rana, Rajiv</searchLink><relatesTo>2</relatesTo><br /><searchLink fieldCode="AR" term="%22Liu%2C+Jong+S%2E%22">Liu, Jong S.</searchLink><relatesTo>2</relatesTo><i> jong.liu@honeywell.com</i>
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  Data: <searchLink fieldCode="JN" term="%22Journal+of+Turbomachinery%22">Journal of Turbomachinery</searchLink>. Sep2015, Vol. 137 Issue 9, p091009-1-091009-11. 11p.
– Name: Subject
  Label: Subjects
  Group: Su
  Data: <searchLink fieldCode="DE" term="%22Gas+turbines%22">Gas turbines</searchLink><br /><searchLink fieldCode="DE" term="%22Heat+transfer%22">Heat transfer</searchLink><br /><searchLink fieldCode="DE" term="%22Heat+flux%22">Heat flux</searchLink><br /><searchLink fieldCode="DE" term="%22Thermal+insulation%22">Thermal insulation</searchLink><br /><searchLink fieldCode="DE" term="%22Computational+fluid+dynamics%22">Computational fluid dynamics</searchLink>
– Name: Abstract
  Label: Abstract
  Group: Ab
  Data: The flow field in axial gas turbines is driven by strong unsteady interactions between stationary and moving components. While time-averaged measurements can highlight many important flow features, developing a deeper understanding of the complicated flows present in high-speed turbomachinery requires time-accurate measurements that capture this unsteady behavior. Toward this end, time-accurate measurements are presented for a fully cooled transonic high-pressure turbine stage operating at designcorrected conditions. The turbine is run in a short-duration blowdown facility with uniform, radial, and hot streak vane-inlet temperature profiles as well as various amounts of cooling flow. High-frequency response surface pressure and heat-flux instrumentation installed in the rotating blade row, stator vane row, and stationary outer shroud provide detailed measurements of the flow behavior for this stage. Previous papers have reported the time-averaged results from this experiment, but this paper focuses on the strong unsteady phenomena that are observed. Heat-flux measurements from double-sided heatflux gauges (HFGs) cover three spanwise locations on the blade pressure and suction surfaces. In addition, there are two instrumented blades with the cooling holes blocked to isolate the effect of just blade cooling. The stage can be run with the vane and blade cooling flow either on or off. High-frequency pressure measurements provide a picture of the unsteady aerodynamics on the vane and blade airfoil surfaces, as well as inside the serpentine coolant supply passages of the blade. A time-accurate computational fluid dynamics (CFD) simulation is also run to predict the blade swface pressure and heatflux, and comparisons between prediction and measurement are given. It is found that unsteady variations in heat-flux and pressure are stronger at low to midspan and weaker at high span, likely due to the impact of secondary flows such as the tip leakage flow. Away from the tip, it is seen that the unsteady fluctuations in pressure and heat-flux are mostly in phase with each other on the suction side, but there is some deviation on the pressure side. The flow field is ultimately shown to be highly three-dimensional, as the movement of high heat transfer regions can be traced in both the chord and spanwise directions. These measurements provide a unique picture of the unsteady flow physics of a rotating turbine, and efforts to better understand and model these time-varying flows have the potential to change the way we think about even the time-averaged flow characteristics. [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.)
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RecordInfo BibRecord:
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    Identifiers:
      – Type: doi
        Value: 10.1115/1.4029950
    Languages:
      – Code: eng
        Text: English
    PhysicalDescription:
      Pagination:
        PageCount: 11
        StartPage: 091009-1
    Subjects:
      – SubjectFull: Gas turbines
        Type: general
      – SubjectFull: Heat transfer
        Type: general
      – SubjectFull: Heat flux
        Type: general
      – SubjectFull: Thermal insulation
        Type: general
      – SubjectFull: Computational fluid dynamics
        Type: general
    Titles:
      – TitleFull: Time-Resolved Heat Transfer and Surface Pressure Measurements for a Fully Cooled Transonic Turbine Stage.
        Type: main
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          Name:
            NameFull: Nickol, Jeremy B.
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            NameFull: Mathison, Randall M.
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            NameFull: Malak, Malak F.
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            NameFull: Rana, Rajiv
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            NameFull: Liu, Jong S.
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          Dates:
            – D: 01
              M: 09
              Text: Sep2015
              Type: published
              Y: 2015
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              Value: 0889504X
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              Value: 137
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              Value: 9
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            – TitleFull: Journal of Turbomachinery
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