0
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
Your Session has timed out. Please sign back in to continue.

References

Schiele, R. , and Wittig, S. , 2000, “ Gas Turbine Heat Transfer: Past and Future Challenges,” J. Propul. Power, 16(4), pp. 583–589. [CrossRef]
Han, J. C. , Dutta, S. , and Ekkad, S. V. , 2000, Gas Turbine Heat Transfer and Cooling Technology, Taylor & Francis, London.
Greenblatt, D. , and Wygnanski, I. J. , 2000, “ The Control of Flow Separation by Periodic Excitation,” Prog. Aerosp. Sci., 36(7), pp. 487–545. [CrossRef]
Rice, E. J. , and Zaman, K. B. M. Q. , 1987, “ Control of Shear Flows by Artificial Excitation,” NASA, Cleveland, OH, AIAA Paper No. 87-2722.
Ahuja, K. K. , and Burrin, R. H. , 1984, “ Control of Flow Separation by Sound,” AIAA Paper No. 84-2298.
Kaiping, P. , 1983, “ Unsteady Forced Convective Heat Transfer From a Hot Film in Non-Reversing and Reversing Shear Flow,” Int. J. Heat Mass Transfer, 26(4), pp. 545–556. [CrossRef]
Fujita, N. , and Tsubouchi, T. , 1982, “ An Experimental Study of Unsteady Heat Transfer From a Flat Plate to an Oscillating Air Flow,” Heat Transfer-Jpn. Res., 11, pp. 31–43.
Cooper, P. I. , Sheridan, J. C. , and Flood, G. J. , 1986, “ The Effects of Sound on Forced Convection Over a Flat Plate,” Int. J. Heat Fluid Flow, 7(1), pp. 61–68. [CrossRef]
Feiler, C. E. , 1964, “ Experimental Heat Transfer and Boundary Layer Behavior With 100-CPS Oscillations,” NASA Technical Note No. 2531.
Park, J. S. , Taylor, M. F. , and McEligot, D. M. , 1982, “ Heat Transfer to Pulsating Turbulent Gas Flow,” Seventh International Heat Transfer Conference, pp. 105–110 http://adsabs.harvard.edu/abs/1982hetr....3..105P.
Purdy, K. R. , Jackson, T. W. , and Gorton, C. W. , 1964, “ Viscous Fluid Flow Under the Influence of a Resonant Acoustic Field,” ASME J. Heat Transfer, 86(1), pp. 97–106. [CrossRef]
Purdy, K. R. , Jackson, T. W. , Willoughby, D. A. , Keith, H. G. , and Willbanks, C. E. , 1965, The Effect of a Resonant Acoustic Field on Laminar Flow in a Circular Tube, Georgia Institute of Technology, Atlanta, GA.
Jackson, T. W. , Purdy, K. R. , Keith, H. G. , and Rudland, R. S. , 1965, Investigations of the Effect of Acoustic Vibrations on Convective Heat Transfer, Georgia Institute of Technology, Atlanta, GA.
Merkli, P. , and Thomann, H. , 1975, “ Thermoacoustic Effects in a Resonance Tube,” J. Fluid Mech., 70(1), pp. 161–177. [CrossRef]
Jackson, T. W. , Oliver, C. C. , and Eastwood, I. , 1961, The Effects of Resonant Vibrations on Heat Transfer at High Reynolds Numbers, Georgia Institute of Technology, Atlanta, GA.
Jackson, T. W. , Harrison, W. B. , and Boteler, W. C. , 1959, “ Free Convection, Forced Convection, and Acoustic Vibrations in a Constant Temperature Vertical Tube,” ASME J. Heat Transfer, 81, pp. 68–74.
Lemich, R. , and Hwu, C. K. , 1961, “ The Effect of Acoustic Vibration on Forced Convective Heat Transfer,” AIChE J., 7(1), pp. 102–106. [CrossRef]
Ahuja, K. K. , Whipkey, R. R. , and Jones, G. S. , 1983, “ Control of Turbulent Boundary Layer Flows by Sound,” AIAA Paper No. 83-0726.
Zaman, K. B. M. Q. , Bar-Sever, A. , and Mangalam, S. M. , 1987, “ Effect of Acoustic Excitation on the Flow Over a Low-Re Airfoil,” J. Fluid Mech., 182, pp. 127–148. [CrossRef]
Denos, R. , Sieverding, C. H. , Arts, T. , Brouckaert, J. F. , Paniagua, G. , and Michelassi, V. , 1999, “ Experimental Investigation of the Unsteady Rotor Aerodynamics of a Transonic Turbine Stage,” Proc. Inst. Mech. Eng., Part A, 213(4), pp. 327–338. [CrossRef]
Denos, R. , and Paniagua, G. , 2005, “ Effect of Vane-Rotor Interaction on the Unsteady Flow Field Downstream of a Transonic High Pressure Turbine,” Proc. Inst. Mech. Eng, Part A, 219(6), pp. 431–442. [CrossRef]
Collins, M. , and Povey, T. , 2014, “ Exploitation of Acoustic Effects in Film Cooling,” ASME Paper No. GT2014-26318.
Halila, E. E. , Lenahan, D. T. , and Thomas, T. T. , 1982, “ High Pressure Turbine Test Hardware Detailed Design Report,” NASA-Lewis Research Center, Report No. NASA-CR-167955.
Zhang, Y. M. , Gu, W. Z. , and Han, J. C. , 1994, “ Heat Transfer and Friction in Rectangular Channels With Ribbed or Ribbed-Grooved Walls,” ASME J. Heat Transfer, 116(1), pp. 58–65. [CrossRef]
Crocker, M. J. , 2008, Handbook of Acoustics, Wiley-IEEE, Hoboken, NJ.
Bauer, A. B. , 1977, “ Impedance Theory and Measurements on a Porous Acoustic Liner,” AIAA J. Aircr., 14(8), pp. 720–728. [CrossRef]
Cukurel, B. , Selcan, C. , and Arts, T. , 2013, “ Film Cooling Extraction Effects on the Aero-Thermal Characteristics of Rib Roughened Cooling Channel Flow,” ASME J. Turbomach., 135(2), p. 021016. [CrossRef]
Cukurel, B. , Selcan, C. , and Arts, T. , 2012, “ Color Theory Perception of Steady Wide Band Liquid Crystal Thermometry,” Exp. Therm. Fluid Sci., 39, pp. 112–122. [CrossRef]
de Brederode, V. , and Bradshaw, P. , 1972, “ Three-Dimensional Flow in Nominally Two-Dimensional Separation Bubbles: 1. Flow Behind a Rearward-Facing Step,” Imperial College of Science and Technology, Department of Aeronautics, London, UK, Report No. Aero Report 72-19.
Casarsa, L. , and Arts, T. , 2005, “ Experimental Investigation of the Aerothermal Performance of a High Blockage Rib-Roughened Cooling Channel,” ASME J. Turbomach., 127(3), pp. 580–588. [CrossRef]
Sparrow, E. M. , Kang, S. S. , and Chuck, W. , 1987, “ Relation Between the Points of Flow Reattachment and Maximum Heat Transfer for Regions of Flow Separation,” Int. J. Heat Mass Transfer, 30(7), pp. 1237–1246. [CrossRef]
Zukauskas, V. A. , and Pedisius, K. A. , 1987, “ Heat Transfer to Reattached Fluid Flow Downstream of a Fence,” Wärme Stoffübertragung, 21(2), pp. 125–131. [CrossRef]
Inaoka, K. , Kakamura, K. , and Senda, M. , 2004, “ Heat Transfer Control of a Backward-Facing Step Flow in a Duct by Means of Miniature Electromagnetic Actuators,” Int. J. Heat Fluid Flow, 25(5), pp. 711–720. [CrossRef]
Bhattacharjee, S. , Scheelke, B. , and Troutt, T. R. , 1986, “ Modification of Vortex Interactions in a Reattaching Separated Flow,” AIAA J, 24(4), pp. 623–629. [CrossRef]
Han, J. C. , Glicksman, L. R. , and Rohsenow, W. M. , 1978, “ An Investigation of Heat Transfer and Friction for Rib-Roughened Surfaces,” Int. J. Heat Mass Transfer, 21(8), pp. 1143–1156. [CrossRef]
Taslim, M. E. , and Springs, S. D. , 1994, “ Effect of Turbulator Profile and Spacing on Heat Transfer and Friction in a Channel,” AIAA J. Thermophys. Heat Transfer, 8(3), pp. 555–562. [CrossRef]
Ichiyima, K. , Yokoyama, M. , and Shimomura, R. , 1983, “ Effects of Several Roughness Elements for the Heat Transfer From a Smooth Heated Wall,” ASME/JSME Thermal Engineering Joint Conference, pp. 359–364.

Figures

Grahic Jump Location
Fig. 1

HPT blade computational domain

Grahic Jump Location
Fig. 2

Schematic of the experimental facility

Grahic Jump Location
Fig. 3

Wind tunnel facility computational domain

Grahic Jump Location
Fig. 4

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

Grahic Jump Location
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

Grahic Jump Location
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

Grahic Jump Location
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

Grahic Jump Location
Fig. 8

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

Grahic Jump Location
Fig. 9

Normalized total acoustic pressure at 126 Hz excitation

Grahic Jump Location
Fig. 10

Normalized total acoustic pressure at 167 Hz excitation

Grahic Jump Location
Fig. 11

SPL variation inside the test section

Grahic Jump Location
Fig. 17

120 Hz centerline static pressure development

Grahic Jump Location
Fig. 16

120 Hz excitation NuD running average

Grahic Jump Location
Fig. 15

120 Hz excitation enhancement factor

Grahic Jump Location
Fig. 14

120 Hz centerline NuD comparison

Grahic Jump Location
Fig. 13

120 Hz excited NuD distribution

Grahic Jump Location
Fig. 12

Baseline unexcited NuD distribution

Tables

Errata

Discussions

Some tools below are only available to our subscribers or users with an online account.

Related Content

Customize your page view by dragging and repositioning the boxes below.

Related Journal Articles
Related eBook Content
Topic Collections

Sorry! You do not have access to this content. For assistance or to subscribe, please contact us:

  • TELEPHONE: 1-800-843-2763 (Toll-free in the USA)
  • EMAIL: asmedigitalcollection@asme.org
Sign In