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    Ceramic Matrix Composite Combustor Liners: A Summary of Field Evaluations

    Source: Journal of Engineering for Gas Turbines and Power:;2007:;volume( 129 ):;issue: 001::page 21
    Author:
    Mark van Roode
    ,
    Jeff Price
    ,
    Josh Kimmel
    ,
    Naren Miriyala
    ,
    Don Leroux
    ,
    Anthony Fahme
    ,
    Kenneth Smith
    DOI: 10.1115/1.2181182
    Publisher: The American Society of Mechanical Engineers (ASME)
    Abstract: Solar Turbines Incorporated, under U.S. government sponsored programs, has been evaluating ceramic matrix composite combustor liners in test rigs and Solar’s Centaur® 50S gas turbine engines since 1992. The objective is to evaluate and improve the performance and durability of CMCs as high-temperature materials for advanced low emissions combustors. Field testing of CMC combustor liners started in May of 1997 and by the end of 2004, over 67,000 operating hours had been accumulated on SiC∕SiC and oxide∕oxide CMC liners. NOx and CO emissions have been consistently <15ppmv and <10ppmv, respectively. Maximum test durations of 15,144h and 13,937h have been logged for SiC∕SiC liners with protective environmental barrier coatings. An oxide∕oxide CMC liner with a Friable Graded Insulation coating has been tested for 12,582h. EBCs significantly improve SiC∕SiC CMC liner life. The basic three-layer EBC consists of consecutive layers of Si, mullite, and BSAS. The durability of the baseline EBC can be improved by mixing BSAS with mullite in the intermediate coating layer. The efficacy of replacing BSAS with SAS has not been demonstrated yet. Heavy degradation was observed for two-layer Si∕BSAS and Si∕SAS EBCs, indicating that the elimination of the intermediate layer is detrimental to EBC durability. Equivalent performance was observed when the Hi-Nicalon fiber reinforcement was replaced with Tyranno ZM or ZMI fiber. Melt infiltrated SiC∕SiC CMCs have improved durability compared to SiC∕SiC CMCs fabricated by Chemical Vapor Infiltration of the matrix, in the absence of an EBC. However, the presence of an EBC results in roughly equivalent service life for MI and CVI CMCs. Results to date indicate that oxide∕oxide CMCs with protective FGI show minor degradation under Centaur® 50S gas turbine engine operating conditions. The results of, and lessons learned from CMC combustor liner engine field testing, conducted through 2004, have been summarized.
    keyword(s): Engines , Ceramic matrix composites , Combustion chambers AND Testing ,
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      Ceramic Matrix Composite Combustor Liners: A Summary of Field Evaluations

    URI
    https://yetl.yabesh.ir/yetl1/handle/yetl/135766
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    • Journal of Engineering for Gas Turbines and Power

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    contributor authorMark van Roode
    contributor authorJeff Price
    contributor authorJosh Kimmel
    contributor authorNaren Miriyala
    contributor authorDon Leroux
    contributor authorAnthony Fahme
    contributor authorKenneth Smith
    date accessioned2017-05-09T00:23:47Z
    date available2017-05-09T00:23:47Z
    date copyrightJanuary, 2007
    date issued2007
    identifier issn1528-8919
    identifier otherJETPEZ-26935#21_1.pdf
    identifier urihttp://yetl.yabesh.ir/yetl/handle/yetl/135766
    description abstractSolar Turbines Incorporated, under U.S. government sponsored programs, has been evaluating ceramic matrix composite combustor liners in test rigs and Solar’s Centaur® 50S gas turbine engines since 1992. The objective is to evaluate and improve the performance and durability of CMCs as high-temperature materials for advanced low emissions combustors. Field testing of CMC combustor liners started in May of 1997 and by the end of 2004, over 67,000 operating hours had been accumulated on SiC∕SiC and oxide∕oxide CMC liners. NOx and CO emissions have been consistently <15ppmv and <10ppmv, respectively. Maximum test durations of 15,144h and 13,937h have been logged for SiC∕SiC liners with protective environmental barrier coatings. An oxide∕oxide CMC liner with a Friable Graded Insulation coating has been tested for 12,582h. EBCs significantly improve SiC∕SiC CMC liner life. The basic three-layer EBC consists of consecutive layers of Si, mullite, and BSAS. The durability of the baseline EBC can be improved by mixing BSAS with mullite in the intermediate coating layer. The efficacy of replacing BSAS with SAS has not been demonstrated yet. Heavy degradation was observed for two-layer Si∕BSAS and Si∕SAS EBCs, indicating that the elimination of the intermediate layer is detrimental to EBC durability. Equivalent performance was observed when the Hi-Nicalon fiber reinforcement was replaced with Tyranno ZM or ZMI fiber. Melt infiltrated SiC∕SiC CMCs have improved durability compared to SiC∕SiC CMCs fabricated by Chemical Vapor Infiltration of the matrix, in the absence of an EBC. However, the presence of an EBC results in roughly equivalent service life for MI and CVI CMCs. Results to date indicate that oxide∕oxide CMCs with protective FGI show minor degradation under Centaur® 50S gas turbine engine operating conditions. The results of, and lessons learned from CMC combustor liner engine field testing, conducted through 2004, have been summarized.
    publisherThe American Society of Mechanical Engineers (ASME)
    titleCeramic Matrix Composite Combustor Liners: A Summary of Field Evaluations
    typeJournal Paper
    journal volume129
    journal issue1
    journal titleJournal of Engineering for Gas Turbines and Power
    identifier doi10.1115/1.2181182
    journal fristpage21
    journal lastpage30
    identifier eissn0742-4795
    keywordsEngines
    keywordsCeramic matrix composites
    keywordsCombustion chambers AND Testing
    treeJournal of Engineering for Gas Turbines and Power:;2007:;volume( 129 ):;issue: 001
    contenttypeFulltext
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