Research Papers

Determination of Cooling Parameters for a High-Speed, True-Scale, Metallic Turbine Vane

[+] Author and Article Information
Marc D. Polanka

Department of Aeronautical Engineering,
Air Force Institute of Technology,
Dayton, OH 45433
e-mail: Marc.Polanka@afit.edu

James L. Rutledge

Department of Aeronautical Engineering,
Air Force Institute of Technology,
Dayton, OH 45433

David G. Bogard

Department of Mechanical Engineering,
University of Texas,
Austin, TX 78415

Richard J. Anthony

Aerospace Systems Directorate,
Air Force Research Laboratory,
Dayton, OH 45433

Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the JOURNAL OF TURBOMACHINERY. Manuscript received October 21, 2015; final manuscript received June 7, 2016; published online August 2, 2016. Assoc. Editor: Karen A. Thole.This material is declared a work of the U.S. Government and is not subject to copyright protection in the United States. Approved for public release; distribution is unlimited.

J. Turbomach 139(1), 011001 (Aug 02, 2016) (9 pages) Paper No: TURBO-15-1233; doi: 10.1115/1.4033974 History: Received October 21, 2015; Revised June 07, 2016

Facilities such as the Turbine Research Facility (TRF) at the Air Force Research Laboratory have been acquiring uncooled heat transfer measurements on full-scale metallic airfoils for several years. The addition of cooling flow to this type of facility has provided new capabilities and new challenges. Two primary challenges for cooled rotating hardware are that the true local film temperature is unknown, and cooled thin-walled metallic airfoils prohibit semi-infinite heat conduction calculation. Extracting true local adiabatic effectiveness and the heat transfer coefficient from measurements of surface temperature and surface heat transfer is therefore difficult. In contrast, another cooling parameter, the overall effectiveness (ϕ), is readily obtained from the measurements of surface temperature, internal coolant temperature, and mainstream temperature. The overall effectiveness is a normalized measure of surface temperatures expected for actual operating conditions and is thus an important parameter that drives the life expectancy of a turbine component. Another issue is that scaling ϕ from experimental conditions to engine conditions is dependent on the heat transfer through the part. It has been well-established that the Biot number must be matched for the experimentally measured ϕ to match ϕ at engine conditions. However, the thermal conductivity of both the metal blade and the thermal barrier coating changes substantially from low-temperature to high-temperature engine conditions and usually not in the same proportion. This paper describes a novel method of replicating the correct thermal behavior of the thermal barrier coating (TBC) relative to the metal turbine while obtaining surface temperature measurements and heat fluxes. Furthermore, this paper describes how the ϕ value obtained at the low-temperature conditions can be adjusted to predict ϕ at high-temperature engine conditions when it is impossible to match the Biot number perfectly.

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Grahic Jump Location
Fig. 1

Time history of data from Popp et al. [7]

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Fig. 2

Resultant heat transfer coefficient and adiabatic effectiveness from Popp et al. [7]

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Fig. 3

Photograph of the TRF

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Fig. 5

Resultant calculated heat flux and nondimensional surface temperature

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Fig. 4

Temperature histories of relevant parameters for gauge at 15% SS

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Fig. 6

Time-dependant data for gauge at 15% surface length on suction side

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Fig. 7

Method of Popp applied to gauge at 15% surface length on suction side




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