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Research Papers

Implementation of an In-Situ Infrared Calibration Method for Precise Heat Transfer Measurements on a Linear Cascade

[+] Author and Article Information
Svenja Aberle

Institute of Jet Propulsion,
Universität der Bundeswehr München,
Neubiberg 85577, Germany
e-mail: svenja.aberle@unibw.de

Martin Bitter, Reinhard Niehuis

Institute of Jet Propulsion,
Universität der Bundeswehr München,
Neubiberg 85577, Germany

Florian Hoefler, Jorge Carretero Benignos

GE Global Research,
Garching 85748, Germany

1Corresponding author.

Manuscript received February 15, 2018; final manuscript received August 8, 2018; published online January 16, 2019. Assoc. Editor: Coutier-Delgosha Olivier.

J. Turbomach 141(2), 021004 (Jan 16, 2019) (7 pages) Paper No: TURBO-18-1034; doi: 10.1115/1.4041132 History: Received February 15, 2018; Revised August 08, 2018

For heat transfer measurements on the center blade of a linear cascade, the infrared measurement technique was set up. As a highly challenging condition, the angular dependency of the infrared signal was identified. Beside a shallow angle of view, limited by geometric conditions, the curved blade surface necessitated the consideration of this dependency. Therefore, a powerful in-situ calibration method was set up, which accounts for the angular dependency implicitly. In contrast to usual procedures, the correlation of the measured infrared intensity and the temperature was calibrated by a separate calibration function for each position on the blade. In all, three different calibration approaches were proceeded and assessed. Initial measurements in low-speed test conditions delivered physically more reasonable results, using a local calibration compared to a usual global calibration. By means of these data, an evaluation of the aerodynamic characteristic of the cascade was enabled. With few modifications, the procedure is capable to deliver high-precision heat transfer measurements in the high-speed cascade wind-tunnel at the Institute of Jet Propulsion.

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References

Grawunder, M. , Reß, R. , and Breitsamter, C. , 2016, “ Thermographic Transition Detection for Low-Speed Wind-Tunnel Experiments,” AIAA J., 54(6), pp. 2012–2016. [CrossRef]
Carlomagno, G. M. , and Cardone, G. , 2010, “ Infrared Thermography for Convective Heat Transfer Measurements,” Exp. Fluids, 49(6), pp. 1187–1218. [CrossRef]
Gomes, R. , and Niehuis, R. , 2009, “ Film Cooling Effectiveness Measurements on Highly Loaded Blades With Flow Separation,” Eighth European Conference on Turbomachinery, Fluid Dynamics and Thermodynamics, No. 237.
Bitter, M. , 2014, “ Characterization of a Turbulent Separating, Reattaching Flow Using Optical Pressure and Velocity Measurements,” Ph.D. thesis,, Universität der Bundeswehr München, Neubiberg, Germany.
Sargent, S. R. , Hedlund, C. R. , and Ligrani, P. M. , 1998, “ An Infrared Thermography Imaging System for Convective Heat Transfer Measurements in Complex Flows,” Meas. Sci. Technol., 9(12), pp. 1974–1981. [CrossRef]
Schulz, A. , 2000, “ Infrared Thermography as Applied to Film Cooling of Gas Turbine Components,” Meas. Sci. Technol., 11(7), pp. 948–956. [CrossRef]
Vliet, G. C. , 1969, “ Natural Convection Local Heat Transfer on Constant-Heat-Flux Inclined Surfaces,” ASME J. Heat Transfer, 91(4), pp. 511–516. [CrossRef]

Figures

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Fig. 1

Schematic of cascade wind tunnel; airfoils not to scale

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Fig. 2

Integration of electrical connectors and optical accesses into the sidewall; airfoil not to scale

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Fig. 3

Angular dependency of the infrared signal for four different temperature levels on a flat plate

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Fig. 4

Angular effects of the measured infrared intensity during calibration, and allocated temperature distribution for temperature level 5 on the suction side; dimensions not to scale: (a) Illustration of measurement region on the blade, (b) mapped infrared intensity distribution, (c) estimated angle of view, and (d) temperature distribution determined by FEM-simulation

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Fig. 5

Temperature distributions on the suction side used for different calibration processes

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Fig. 6

Illustration of the FEM-simulation for the calculation of the conductive heat flux loss; airfoil not to scale: (a) Case: heated suction side and (b) case: heated pressure side

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Fig. 7

Normalized temperature distribution for operating point 1, evaluated by different calibration approaches

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Fig. 8

Normalized distribution of the heat transfer coefficient for different flow conditions

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Fig. 9

Standard deviation of the measured infrared intensity on the suction side for different operating points

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