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Evolution of Surface Deposits on a High Pressure Turbine Blade: Part II — Convective Heat Transfer

[+] Author Affiliations
Jeffrey P. Bons, James E. Wammack, Jared Crosby, Daniel Fletcher, Thomas H. Fletcher

Brigham Young University, Provo, UT

Paper No. GT2006-91257, pp. 1075-1082; 8 pages
doi:10.1115/GT2006-91257
From:
  • ASME Turbo Expo 2006: Power for Land, Sea, and Air
  • Volume 3: Heat Transfer, Parts A and B
  • Barcelona, Spain, May 8–11, 2006
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 0-7918-4238-X | eISBN: 0-7918-3774-2
  • Copyright © 2006 by ASME

abstract

A TBC-coated turbine blade coupon was exposed to successive deposition in an accelerated deposition facility simulating flow conditions at the inlet to a first stage high pressure turbine (T = 1150°C, M = 0.31). The combustor exit flow was seeded with dust particulate that would typically be ingested by a large utility power plant. The turbine coupon was subjected to four successive 2 hour deposition tests. The particulate loading was scaled to simulate 0.02 ppmw (parts per million weight) of particulate over three months of continuous gas turbine operation for each 2 hour laboratory simulation (for a cumulative one year of operation). Three-dimensional maps of the deposit-roughened surfaces were created between each test, representing a total of four measurements evenly spaced through the lifecycle of a turbine blade surface. From these measurements, scaled models were produced for testing in a low-speed wind tunnel with a turbulent, zero pressure gradient boundary layer at Re = 750,000. The average surface heat transfer coefficient was measured using a transient surface temperature measurement technique. Stanton number increases initially with deposition but then levels off as the surface becomes less peaked. Subsequent deposition exposure then produces a second increase in St. Surface maps of St highlight the local influence of deposit peaks with regard to heat transfer.

Copyright © 2006 by ASME

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