NON-DESTRUCTIVE THERMAL BARRIER COATING SPALLATION PREDICTION BY A LOADBASED MICRO-INDENTATION TECHNIQUE

Tannenbaum, J M; Lee, K; -J Kang, B S; Alvin, M A

Title: NON-DESTRUCTIVE THERMAL BARRIER COATING SPALLATION PREDICTION BY A LOADBASED MICRO-INDENTATION TECHNIQUE

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Abstract

Currently, the durability and life cycle of thermal barrier coatings (TBC) applied to gas turbine blades and combustor components are limiting the maximum temperature and subsequent efficiency at which gas turbine engines operate. The development of new materials, coating technologies and evaluation techniques is required if enhanced efficiency is to be achieved. Of the current ceramic coating materials used in gas turbine engines, yttria stabilized zirconia (YSZ) is most prevalent, its low thermal conductivity, high thermal expansion coefficient and outstanding mechanical strength make it ideal for use in TBC systems. However, residual stresses caused by coefficients of thermal expansion mismatches within the TBC system and unstable thermally grown oxides are considered the primary causes for its premature and erratic spallation failure. Through finite element simulations, it is shown that the residual stresses generated within the thermally grown oxide (TGO), bond coat (BC), YSZ and their interfaces create slight variations in indentation unloading surface stiffness response prior to spallation failure. In this research, seven air plasma sprayed and one electron beam physical vapor deposition yttria partially stabilized zirconia TBCs were subjected to isothermal and cyclic loadings at 1100°C. The associated coating degradation was evaluated using a non-destructive multiple partial unloading micro-indentationmore »« less

Authors:: Tannenbaum, J M; Lee, K; -J Kang, B S; Alvin, M A

Publication Date:: Thu Nov 18 00:00:00 EST 2010

Research Org.:: National Energy Technology Lab. (NETL), Pittsburgh, PA, and Morgantown, WV (United States). In-house Research

Sponsoring Org.:: USDOE Assistant Secretary for Fossil Energy (FE)

OSTI Identifier:: 1015346

Report Number(s):: NETL-TPR-2982
TRN: US201111%%558

DOE Contract Number:: XX0000000

Resource Type:: Conference

Resource Relation:: Conference: ASME International Mechanical Engineering Congress and Exposition; November 12-18, 2010, Vancouver, BC

Country of Publication:: United States

Language:: English

Subject:: 36 MATERIALS SCIENCE; CERAMICS; COATINGS; COMBUSTORS; EFFICIENCY; ELECTRON BEAMS; FLEXIBILITY; FORECASTING; GAS TURBINE ENGINES; GAS TURBINES; LIFE CYCLE; MECHANICAL ENGINEERING; OXIDES; PHYSICAL VAPOR DEPOSITION; RESIDUAL STRESSES; SPALLATION; THERMAL BARRIERS; THERMAL CONDUCTIVITY; THERMAL EXPANSION; UNLOADING

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                    Tannenbaum, J M, Lee, K, -J Kang, B S, and Alvin, M A. NON-DESTRUCTIVE THERMAL BARRIER COATING SPALLATION PREDICTION BY A LOADBASED MICRO-INDENTATION TECHNIQUE.  United States: N. p., 2010. 
        Web.

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                    Tannenbaum, J M, Lee, K, -J Kang, B S, & Alvin, M A. NON-DESTRUCTIVE THERMAL BARRIER COATING SPALLATION PREDICTION BY A LOADBASED MICRO-INDENTATION TECHNIQUE.  United States.

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                    Tannenbaum, J M, Lee, K, -J Kang, B S, and Alvin, M A. 2010.  
        "NON-DESTRUCTIVE THERMAL BARRIER COATING SPALLATION PREDICTION BY A LOADBASED MICRO-INDENTATION TECHNIQUE".  United States.

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@article{osti_1015346,

  title        = {NON-DESTRUCTIVE THERMAL BARRIER COATING SPALLATION PREDICTION BY A LOADBASED MICRO-INDENTATION TECHNIQUE},

  author       = {Tannenbaum, J M and Lee, K and -J Kang, B S and Alvin, M A},

  abstractNote = {Currently, the durability and life cycle of thermal barrier coatings (TBC) applied to gas turbine blades and combustor components are limiting the maximum temperature and subsequent efficiency at which gas turbine engines operate. The development of new materials, coating technologies and evaluation techniques is required if enhanced efficiency is to be achieved. Of the current ceramic coating materials used in gas turbine engines, yttria stabilized zirconia (YSZ) is most prevalent, its low thermal conductivity, high thermal expansion coefficient and outstanding mechanical strength make it ideal for use in TBC systems. However, residual stresses caused by coefficients of thermal expansion mismatches within the TBC system and unstable thermally grown oxides are considered the primary causes for its premature and erratic spallation failure. Through finite element simulations, it is shown that the residual stresses generated within the thermally grown oxide (TGO), bond coat (BC), YSZ and their interfaces create slight variations in indentation unloading surface stiffness response prior to spallation failure. In this research, seven air plasma sprayed and one electron beam physical vapor deposition yttria partially stabilized zirconia TBCs were subjected to isothermal and cyclic loadings at 1100°C. The associated coating degradation was evaluated using a non-destructive multiple partial unloading micro-indentation procedure. The results show that the proposed non-destructive micro-indentation evaluation technique can be an effective and specimenindependent TBC failure prediction tool capable of determining the location of initial spallation failure prior to its actual occurrence.},

  doi          = {},

  url          = {https://www.osti.gov/biblio/1015346},
  journal      = {},
number       = ,

  volume       = ,

  place        = {United States},

  year         = {Thu Nov 18 00:00:00 EST 2010},

  month        = {Thu Nov 18 00:00:00 EST 2010}

}

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