Effects of effusion cooling pattern near the dilution hole for a double-walled combustor liner-part 2: Flowfield measurements

Adam C. Shrager, Karen A. Thole, Dominic Mongillo

Research output: Chapter in Book/Report/Conference proceedingConference contribution

Abstract

The complex flowfield inside a gas turbine combustor creates a difficult challenge in cooling the combustor walls. Many modern combustors are designed with a double-wall that contain both impingement cooling on the backside of the wall and effusion cooling on the external side of the wall. Complicating matters is the fact that these double-walls also contain large dilution holes whereby the cooling film from the effusion holes is interrupted by the high-momentum dilution jets. Given the importance of cooling the entire panel, including the metal surrounding the dilution holes, the focus of this paper is understanding the flow in the region near the dilution holes. Near-wall flowfield measurements are presented for three different effusion cooling hole patterns near the dilution hole. The effusion cooling hole patterns were varied in the region near the dilution hole and include: no effusion holes; effusion holes pointed radially outward from the dilution hole; and effusion holes pointed radially inward toward the dilution hole. Particle image velocimetry (PIV) was used to capture the time-Averaged flowfield at approaching freestream turbulence intensities of 0.5% and 13%. Results showed evidence of downward motion at the leading edge of the dilution hole for all three effusion hole patterns. In comparing the three geometries, the outward effusion holes showed significantly higher velocities toward the leading edge of the dilution jet relative to the other two geometries. Although the flowfield generated by the dilution jet dominated the flow downstream, each cooling hole pattern interacted with the flowfield uniquely. Approaching freestream turbulence did not have a significant effect on the flowfield.

Original languageEnglish (US)
Title of host publicationHeat Transfer
PublisherAmerican Society of Mechanical Engineers (ASME)
ISBN (Print)9780791851104
DOIs
StatePublished - Jan 1 2018
EventASME Turbo Expo 2018: Turbomachinery Technical Conference and Exposition, GT 2018 - Oslo, Norway
Duration: Jun 11 2018Jun 15 2018

Publication series

NameProceedings of the ASME Turbo Expo
Volume5C-2018

Other

OtherASME Turbo Expo 2018: Turbomachinery Technical Conference and Exposition, GT 2018
CountryNorway
CityOslo
Period6/11/186/15/18

Fingerprint

Combustors
Dilution
Cooling
Turbulence
Geometry
Velocity measurement
Gas turbines
Momentum

All Science Journal Classification (ASJC) codes

  • Engineering(all)

Cite this

Shrager, A. C., Thole, K. A., & Mongillo, D. (2018). Effects of effusion cooling pattern near the dilution hole for a double-walled combustor liner-part 2: Flowfield measurements. In Heat Transfer (Proceedings of the ASME Turbo Expo; Vol. 5C-2018). American Society of Mechanical Engineers (ASME). https://doi.org/10.1115/GT2018-77290
Shrager, Adam C. ; Thole, Karen A. ; Mongillo, Dominic. / Effects of effusion cooling pattern near the dilution hole for a double-walled combustor liner-part 2 : Flowfield measurements. Heat Transfer. American Society of Mechanical Engineers (ASME), 2018. (Proceedings of the ASME Turbo Expo).
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abstract = "The complex flowfield inside a gas turbine combustor creates a difficult challenge in cooling the combustor walls. Many modern combustors are designed with a double-wall that contain both impingement cooling on the backside of the wall and effusion cooling on the external side of the wall. Complicating matters is the fact that these double-walls also contain large dilution holes whereby the cooling film from the effusion holes is interrupted by the high-momentum dilution jets. Given the importance of cooling the entire panel, including the metal surrounding the dilution holes, the focus of this paper is understanding the flow in the region near the dilution holes. Near-wall flowfield measurements are presented for three different effusion cooling hole patterns near the dilution hole. The effusion cooling hole patterns were varied in the region near the dilution hole and include: no effusion holes; effusion holes pointed radially outward from the dilution hole; and effusion holes pointed radially inward toward the dilution hole. Particle image velocimetry (PIV) was used to capture the time-Averaged flowfield at approaching freestream turbulence intensities of 0.5{\%} and 13{\%}. Results showed evidence of downward motion at the leading edge of the dilution hole for all three effusion hole patterns. In comparing the three geometries, the outward effusion holes showed significantly higher velocities toward the leading edge of the dilution jet relative to the other two geometries. Although the flowfield generated by the dilution jet dominated the flow downstream, each cooling hole pattern interacted with the flowfield uniquely. Approaching freestream turbulence did not have a significant effect on the flowfield.",
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Shrager, AC, Thole, KA & Mongillo, D 2018, Effects of effusion cooling pattern near the dilution hole for a double-walled combustor liner-part 2: Flowfield measurements. in Heat Transfer. Proceedings of the ASME Turbo Expo, vol. 5C-2018, American Society of Mechanical Engineers (ASME), ASME Turbo Expo 2018: Turbomachinery Technical Conference and Exposition, GT 2018, Oslo, Norway, 6/11/18. https://doi.org/10.1115/GT2018-77290

Effects of effusion cooling pattern near the dilution hole for a double-walled combustor liner-part 2 : Flowfield measurements. / Shrager, Adam C.; Thole, Karen A.; Mongillo, Dominic.

Heat Transfer. American Society of Mechanical Engineers (ASME), 2018. (Proceedings of the ASME Turbo Expo; Vol. 5C-2018).

Research output: Chapter in Book/Report/Conference proceedingConference contribution

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Shrager AC, Thole KA, Mongillo D. Effects of effusion cooling pattern near the dilution hole for a double-walled combustor liner-part 2: Flowfield measurements. In Heat Transfer. American Society of Mechanical Engineers (ASME). 2018. (Proceedings of the ASME Turbo Expo). https://doi.org/10.1115/GT2018-77290