Turbine blade coupons with three different surface treatments were exposed to deposition conditions in an accelerated deposition facility. The facility simulates the flow conditions at the inlet to a first stage high-pressure turbine (, ). The combustor exit flow is seeded with dust particulate that would typically be ingested by a large utility power plant. The three coupon surface treatments included: (1) bare polished metal; (2) polished thermal barrier coating with bondcoat; and (3) unpolished oxidation resistant bondcoat. Each coupon was subjected to four successive deposition tests. The particulate loading was scaled to simulate 0.02 parts per million weight (ppmw) of particulate over of continuous gas turbine operation for each laboratory simulation (for a cumulative 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 the surface topology and roughness statistics were determined. Despite the different surface treatments, all three surfaces exhibited similar nonmonotonic changes in roughness with repeated exposure. In each case, an initial buildup of isolated roughness peaks was followed by a period when valleys between peaks were filled with subsequent deposition. This trend is well documented using the average forward facing roughness angle in combination with the average roughness height as characteristic roughness metrics. Deposition-related mechanisms leading to spallation of the thermal barrier coated coupons are identified and documented.
Skip Nav Destination
Article navigation
April 2008
Research Papers
Evolution of Surface Deposits on a High-Pressure Turbine Blade—Part I: Physical Characteristics
James E. Wammack,
James E. Wammack
Department of Mechanical Engineering,
Brigham Young University
, Provo, UT 84602
Search for other works by this author on:
Jared Crosby,
Jared Crosby
Department of Mechanical Engineering,
Brigham Young University
, Provo, UT 84602
Search for other works by this author on:
Daniel Fletcher,
Daniel Fletcher
Department of Mechanical Engineering,
Brigham Young University
, Provo, UT 84602
Search for other works by this author on:
Jeffrey P. Bons,
Jeffrey P. Bons
Department of Mechanical Engineering,
Brigham Young University
, Provo, UT 84602
Search for other works by this author on:
Thomas H. Fletcher
Thomas H. Fletcher
Department of Chemical Engineering,
Brigham Young University
, Provo, UT 84602
Search for other works by this author on:
James E. Wammack
Department of Mechanical Engineering,
Brigham Young University
, Provo, UT 84602
Jared Crosby
Department of Mechanical Engineering,
Brigham Young University
, Provo, UT 84602
Daniel Fletcher
Department of Mechanical Engineering,
Brigham Young University
, Provo, UT 84602
Jeffrey P. Bons
Department of Mechanical Engineering,
Brigham Young University
, Provo, UT 84602
Thomas H. Fletcher
Department of Chemical Engineering,
Brigham Young University
, Provo, UT 84602J. Turbomach. Apr 2008, 130(2): 021020 (8 pages)
Published Online: March 25, 2008
Article history
Received:
September 8, 2006
Revised:
November 14, 2006
Published:
March 25, 2008
Connected Content
A companion article has been published:
Evolution of Surface Deposits on a High-Pressure Turbine Blade—Part II: Convective Heat Transfer
Citation
Wammack, J. E., Crosby, J., Fletcher, D., Bons, J. P., and Fletcher, T. H. (March 25, 2008). "Evolution of Surface Deposits on a High-Pressure Turbine Blade—Part I: Physical Characteristics." ASME. J. Turbomach. April 2008; 130(2): 021020. https://doi.org/10.1115/1.2752182
Download citation file:
Get Email Alerts
Evaluating Thin-Film Thermocouple Performance on Additively Manufactured Turbine Airfoils
J. Turbomach (July 2025)
Thermohydraulic Performance and Flow Structures of Diamond Pyramid Arrays
J. Turbomach (July 2025)
Related Articles
Role of Platinum in Thermal Barrier Coatings Used in Gas Turbine Blade Applications
J. Eng. Gas Turbines Power (February,2010)
Improved Performance Rhenium Containing Single Crystal Alloy Turbine Blades Utilizing PPM Levels of the Highly Reactive Elements Lanthanum and Yttrium
J. Eng. Gas Turbines Power (January,1999)
Experimental Simulation of a Film Cooled Turbine Blade Leading Edge Including Thermal Barrier Coating Effects
J. Turbomach (January,2011)
Manufacturing Optimization for Bondcoat/Thermal Barrier Coating Systems
J. Eng. Gas Turbines Power (February,2010)
Related Proceedings Papers
Related Chapters
Surface Analysis and Tools
Tribology of Mechanical Systems: A Guide to Present and Future Technologies
Outlook
Closed-Cycle Gas Turbines: Operating Experience and Future Potential
Combined Cycle Power Plant
Energy and Power Generation Handbook: Established and Emerging Technologies