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Research Papers: Heat Transfer Enhancement

Heat Transfer Implications of Acoustic Resonances in Turbine Internal Cooling Channels

[+] Author and Article Information
C. Selcan

Turbomachinery and Heat Transfer Laboratory,
Faculty of Aerospace Engineering,
Technion-Israel Institute of Technology,
Technion City,
Haifa 32000, Israel
e-mail: selcacfv@t2.technion.ac.il

B. Cukurel

Turbomachinery and Heat Transfer Laboratory,
Faculty of Aerospace Engineering,
Technion-Israel Institute of Technology,
Technion City,
Haifa 32000, Israel
e-mail: beni@cukurel.org

J. Shashank

Turbomachinery and Heat Transfer Laboratory,
Faculty of Aerospace Engineering,
Technion-Israel Institute of Technology,
Technion City,
Haifa 32000, Israel
e-mail: judah@tx.technion.ac.il

1Corresponding author.

Contributed by the Heat Transfer Division of ASME for publication in the JOURNAL OF HEAT TRANSFER. Manuscript received January 15, 2015; final manuscript received December 21, 2015; published online February 3, 2016. Assoc. Editor: Jim A. Liburdy.

J. Heat Transfer 138(5), 051902 (Feb 03, 2016) (13 pages) Paper No: HT-15-1035; doi: 10.1115/1.4032331 History: Received January 15, 2015; Revised December 21, 2015

In an attempt to investigate the acoustic resonance effect of serpentine passages on internal convection heat transfer, the present work examines a typical high pressure turbine (HPT) blade internal cooling system, based on the geometry of the NASA E3 engine. In order to identify the associated dominant acoustic characteristics, a numerical finite-element method (FEM) simulation (two-step frequency domain analysis) is conducted to solve the Helmholtz equation with and without source terms. Mode shapes of the relevant identified eigenfrequencies (in the 0–20 kHz range) are studied with respect to induced standing sound wave patterns and the local node/antinode distributions. It is observed that despite the complexity of engine geometries, the predominant resonance behavior can be modeled by a same-ended straight duct. Therefore, capturing the physics observed in a generic geometry, the heat transfer ramifications are experimentally investigated in a scaled wind tunnel facility at a representative resonance condition. Focusing on the straight cooling channel's longitudinal eigenmode in the presence of an isolated rib element, the impact of standing sound waves on convective heat transfer and aerodynamic losses are demonstrated by liquid crystal thermometry, local static pressure and sound level measurements. The findings indicate a pronounced heat transfer influence in the rib wake separation region, without a higher pressure drop penalty. This highlights the potential of modulating the aerothermal performance of the system via acoustic resonance mode excitations.

Copyright © 2016 by ASME
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References

Figures

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Fig. 1

HPT blade computational domain

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Fig. 2

Schematic of the experimental facility

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Fig. 3

Wind tunnel facility computational domain

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Fig. 4

Illustration of the experimental configuration: (a) side view and (b) top view

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Fig. 5

Forward/aft serpentine transmission loss—HP1:2484; HP2: 4263; HP3: 6725; HP4: 9013; HP5: 12208; HP6: 13649; HP7: 15209 Hz; LP1: 2174; LP2: 4669; LP3: 6343; LP4: 8732; LP5: 10783; LP6: 13568; LP7: 14913 Hz

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Fig. 6

Forward serpentine and LE cavity resonance modes (normalized total acoustic pressure): (a) 2484 Hz, (b) 4263 Hz, (c) 6725 Hz, (d) 9013 Hz, (e) 12,208 Hz, (f) 13,649 Hz, (g) 15,209 Hz, (h) 10,675 Hz, (i) 17,332 Hz, (j) 18,196 Hz, (k) 18,475 Hz, and (l) 20,410 Hz

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Fig. 7

Aft serpentine and TE cavity resonance modes (normalized total acoustic pressure): (a) 2174 Hz, (b) 4669 Hz, (c) 6343 Hz, (d) 8732 Hz, (e) 10,783 Hz, (f) 13,568 Hz, (g) 14,913 Hz, (h) 19,491 Hz, (i) 5588 Hz, (j)10,890 Hz, (k)15,815 Hz, and (l)18,933 Hz

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Fig. 8

Defeatured serpentine (normalized total acoustic pressure) (a) 6725 Hz, (b) 6699 Hz, (c) 6518 Hz, and (d) 6490 Hz

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Fig. 9

Normalized total acoustic pressure at 126 Hz excitation

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Fig. 10

Normalized total acoustic pressure at 167 Hz excitation

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Fig. 11

SPL variation inside the test section

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Fig. 12

Baseline unexcited NuD distribution

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Fig. 13

120 Hz excited NuD distribution

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Fig. 14

120 Hz centerline NuD comparison

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Fig. 15

120 Hz excitation enhancement factor

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Fig. 16

120 Hz excitation NuD running average

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Fig. 17

120 Hz centerline static pressure development

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