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@ARTICLE{Mack:838064,
      author       = {Mack, Daniel E. and Wobst, Tanja and Jarligo, Maria Ophelia
                      D. and Sebold, Doris and Vaßen, Robert},
      title        = {{L}ifetime and failure modes of plasma sprayed thermal
                      barrier coatings in thermal gradient rig tests with
                      simultaneous {CMAS} injection},
      journal      = {Surface and coatings technology},
      volume       = {324},
      issn         = {0257-8972},
      address      = {Amsterdam [u.a.]},
      publisher    = {Elsevier Science},
      reportid     = {FZJ-2017-06802},
      pages        = {36 - 47},
      year         = {2017},
      abstract     = {Degradation of thermal barrier coatings (TBCs) in
                      gas-turbine engines due to
                      calcium–magnesium–aluminosilicate (CMAS) glassy deposits
                      from various sources such as sand, volcanic ash, fly ash, or
                      variable quality fuels has been a tenacious issue during the
                      recent years. This follows from the fact that engines are
                      required to operate under increasingly harsh conditions in
                      all kind of gas turbine applications following the demands
                      for higher efficiency and operational flexibility. While the
                      understanding of the mechanism of CMAS induced degradation
                      of TBCs as well as approaches for mitigation of CMAS attack
                      by means of advanced TBC compositions have grown remarkably,
                      most of the reported results have been obtained from lab
                      testing at isothermal conditions or from evaluation of
                      ex-service components, either. The isothermal tests are not
                      reproducing important thermomechanical effects from service
                      conditions, and it may be hard to figure out the thermal
                      history of the ex-service examples.In this study a burner
                      rig facility has been used for the evaluation of TBC
                      performance, where a thermal gradient is applied across the
                      TBC at cyclic load and CMAS is continuously injected to the
                      combustion environment to simulate the conditions closer to
                      actual service in an engine while allowing control of
                      important degradation limiting parameters. Tests have been
                      performed on the state of the art material YSZ while loading
                      parameters as high temperature dwell time and CMAS
                      deposition rate have been varied. Tests have been evaluated
                      in terms of chemical degradation, failure mode and TBC
                      spallation lifetime by means of SEM, EDS and XRD. Test
                      conditions and relevance to in-service operating conditions
                      are discussed. Major impacts on thermal gradient cycling
                      lifetime and similarities and discrepancies related to
                      reported failure mechanism are reviewed.},
      cin          = {IEK-1},
      ddc          = {620},
      cid          = {I:(DE-Juel1)IEK-1-20101013},
      pnm          = {113 - Methods and Concepts for Material Development
                      (POF3-113)},
      pid          = {G:(DE-HGF)POF3-113},
      typ          = {PUB:(DE-HGF)16},
      UT           = {WOS:000406988200005},
      doi          = {10.1016/j.surfcoat.2017.04.071},
      url          = {https://juser.fz-juelich.de/record/838064},
}