Endwall heat transfer for a turbine blade with an upstream cavity and rim seal leakage

Stephen P. Lynch, Karen A. Thole, Atul Kohli, Christopher Lehane, Tom Praisner

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

8 Citations (Scopus)

Abstract

Aerodynamic loss and endwall heat transfer for a turbine blade are influenced by complex vortical flows that are generated at the airfoil-endwall junction. In an engine, those flows interact with clearance gaps between stationary and rotating components, as well as with leakage flow that is designed to exhaust through the gaps. This paper describes experimental measurements of endwall heat transfer for a high-pressure turbine blade with an endwall overlap geometry, as well as an upstream leakage feature that supplied swirled or unswirled leakage relative to the blade. For unswirled leakage, increasing its mass flow increased the magnitude and pitchwise uniformity of the heat transfer coefficient upstream of the blades although heat transfer further into the passage was unchanged. Leakage flow with swirl shifted the horseshoe vortex in the direction of swirl and increased heat transfer on the upstream blade endwall, as compared to unswirled leakage. For a nominal leakage mass flow ratio of 0.75%, swirled leakage did not increase area-averaged heat transfer relative to unswirled leakage. At a mass flow ratio of 1.0%, however, swirled leakage increased overall heat transfer by 4% due to an increase in the strength of the vortical flows.

Original languageEnglish (US)
Title of host publicationASME Turbo Expo 2013
Subtitle of host publicationTurbine Technical Conference and Exposition, GT 2013
DOIs
StatePublished - Dec 17 2013
EventASME Turbo Expo 2013: Turbine Technical Conference and Exposition, GT 2013 - San Antonio, Tx, United States
Duration: Jun 3 2013Jun 7 2013

Publication series

NameProceedings of the ASME Turbo Expo
Volume3 C

Other

OtherASME Turbo Expo 2013: Turbine Technical Conference and Exposition, GT 2013
CountryUnited States
CitySan Antonio, Tx
Period6/3/136/7/13

Fingerprint

Turbomachine blades
Seals
Turbines
Heat transfer
Airfoils
Heat transfer coefficients
Aerodynamics
Vortex flow
Engines
Geometry

All Science Journal Classification (ASJC) codes

  • Engineering(all)

Cite this

Lynch, S. P., Thole, K. A., Kohli, A., Lehane, C., & Praisner, T. (2013). Endwall heat transfer for a turbine blade with an upstream cavity and rim seal leakage. In ASME Turbo Expo 2013: Turbine Technical Conference and Exposition, GT 2013 (Proceedings of the ASME Turbo Expo; Vol. 3 C). https://doi.org/10.1115/GT2013-94942
Lynch, Stephen P. ; Thole, Karen A. ; Kohli, Atul ; Lehane, Christopher ; Praisner, Tom. / Endwall heat transfer for a turbine blade with an upstream cavity and rim seal leakage. ASME Turbo Expo 2013: Turbine Technical Conference and Exposition, GT 2013. 2013. (Proceedings of the ASME Turbo Expo).
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abstract = "Aerodynamic loss and endwall heat transfer for a turbine blade are influenced by complex vortical flows that are generated at the airfoil-endwall junction. In an engine, those flows interact with clearance gaps between stationary and rotating components, as well as with leakage flow that is designed to exhaust through the gaps. This paper describes experimental measurements of endwall heat transfer for a high-pressure turbine blade with an endwall overlap geometry, as well as an upstream leakage feature that supplied swirled or unswirled leakage relative to the blade. For unswirled leakage, increasing its mass flow increased the magnitude and pitchwise uniformity of the heat transfer coefficient upstream of the blades although heat transfer further into the passage was unchanged. Leakage flow with swirl shifted the horseshoe vortex in the direction of swirl and increased heat transfer on the upstream blade endwall, as compared to unswirled leakage. For a nominal leakage mass flow ratio of 0.75{\%}, swirled leakage did not increase area-averaged heat transfer relative to unswirled leakage. At a mass flow ratio of 1.0{\%}, however, swirled leakage increased overall heat transfer by 4{\%} due to an increase in the strength of the vortical flows.",
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Lynch, SP, Thole, KA, Kohli, A, Lehane, C & Praisner, T 2013, Endwall heat transfer for a turbine blade with an upstream cavity and rim seal leakage. in ASME Turbo Expo 2013: Turbine Technical Conference and Exposition, GT 2013. Proceedings of the ASME Turbo Expo, vol. 3 C, ASME Turbo Expo 2013: Turbine Technical Conference and Exposition, GT 2013, San Antonio, Tx, United States, 6/3/13. https://doi.org/10.1115/GT2013-94942

Endwall heat transfer for a turbine blade with an upstream cavity and rim seal leakage. / Lynch, Stephen P.; Thole, Karen A.; Kohli, Atul; Lehane, Christopher; Praisner, Tom.

ASME Turbo Expo 2013: Turbine Technical Conference and Exposition, GT 2013. 2013. (Proceedings of the ASME Turbo Expo; Vol. 3 C).

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

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N2 - Aerodynamic loss and endwall heat transfer for a turbine blade are influenced by complex vortical flows that are generated at the airfoil-endwall junction. In an engine, those flows interact with clearance gaps between stationary and rotating components, as well as with leakage flow that is designed to exhaust through the gaps. This paper describes experimental measurements of endwall heat transfer for a high-pressure turbine blade with an endwall overlap geometry, as well as an upstream leakage feature that supplied swirled or unswirled leakage relative to the blade. For unswirled leakage, increasing its mass flow increased the magnitude and pitchwise uniformity of the heat transfer coefficient upstream of the blades although heat transfer further into the passage was unchanged. Leakage flow with swirl shifted the horseshoe vortex in the direction of swirl and increased heat transfer on the upstream blade endwall, as compared to unswirled leakage. For a nominal leakage mass flow ratio of 0.75%, swirled leakage did not increase area-averaged heat transfer relative to unswirled leakage. At a mass flow ratio of 1.0%, however, swirled leakage increased overall heat transfer by 4% due to an increase in the strength of the vortical flows.

AB - Aerodynamic loss and endwall heat transfer for a turbine blade are influenced by complex vortical flows that are generated at the airfoil-endwall junction. In an engine, those flows interact with clearance gaps between stationary and rotating components, as well as with leakage flow that is designed to exhaust through the gaps. This paper describes experimental measurements of endwall heat transfer for a high-pressure turbine blade with an endwall overlap geometry, as well as an upstream leakage feature that supplied swirled or unswirled leakage relative to the blade. For unswirled leakage, increasing its mass flow increased the magnitude and pitchwise uniformity of the heat transfer coefficient upstream of the blades although heat transfer further into the passage was unchanged. Leakage flow with swirl shifted the horseshoe vortex in the direction of swirl and increased heat transfer on the upstream blade endwall, as compared to unswirled leakage. For a nominal leakage mass flow ratio of 0.75%, swirled leakage did not increase area-averaged heat transfer relative to unswirled leakage. At a mass flow ratio of 1.0%, however, swirled leakage increased overall heat transfer by 4% due to an increase in the strength of the vortical flows.

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Lynch SP, Thole KA, Kohli A, Lehane C, Praisner T. Endwall heat transfer for a turbine blade with an upstream cavity and rim seal leakage. In ASME Turbo Expo 2013: Turbine Technical Conference and Exposition, GT 2013. 2013. (Proceedings of the ASME Turbo Expo). https://doi.org/10.1115/GT2013-94942