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    Gas Turbine Heat Transfer: Ten Remaining Hot Gas Path Challenges

    Source: Journal of Turbomachinery:;2007:;volume( 129 ):;issue: 002::page 193
    Author:
    Ronald S. Bunker
    DOI: 10.1115/1.2464142
    Publisher: The American Society of Mechanical Engineers (ASME)
    Abstract: The advancement of turbine cooling has allowed engine design to exceed normal material temperature limits, but it has introduced complexities that have accentuated the thermal issues greatly. Cooled component design has consistently trended in the direction of higher heat loads, higher through-wall thermal gradients, and higher in-plane thermal gradients. The present discussion seeks to identify ten major thermal issues, or opportunities, that remain for the turbine hot gas path (HGP) today. These thermal challenges are commonly known in their broadest forms, but some tend to be little discussed in a direct manner relevant to gas turbines. These include uniformity of internal cooling, ultimate film cooling, microcooling, reduced incident heat flux, secondary flows as prime cooling, contoured gas paths, thermal stress reduction, controlled cooling, low emission combustor-turbine systems, and regenerative cooling. Evolutionary or revolutionary advancements concerning these issues will ultimately be required in realizable engineering forms for gas turbines to breakthrough to new levels of performance. Herein lies the challenge to researchers and designers. It is the intention of this summary to provide a concise review of these issues, and some of the recent solution directions, as an initial guide and stimulation to further research.
    keyword(s): Cooling , Turbines , Flow (Dynamics) , Gas turbines , Design AND Heat transfer ,
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      Gas Turbine Heat Transfer: Ten Remaining Hot Gas Path Challenges

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    http://yetl.yabesh.ir/yetl1/handle/yetl/137052
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    contributor authorRonald S. Bunker
    date accessioned2017-05-09T00:26:13Z
    date available2017-05-09T00:26:13Z
    date copyrightApril, 2007
    date issued2007
    identifier issn0889-504X
    identifier otherJOTUEI-28736#193_1.pdf
    identifier urihttp://yetl.yabesh.ir/yetl/handle/yetl/137052
    description abstractThe advancement of turbine cooling has allowed engine design to exceed normal material temperature limits, but it has introduced complexities that have accentuated the thermal issues greatly. Cooled component design has consistently trended in the direction of higher heat loads, higher through-wall thermal gradients, and higher in-plane thermal gradients. The present discussion seeks to identify ten major thermal issues, or opportunities, that remain for the turbine hot gas path (HGP) today. These thermal challenges are commonly known in their broadest forms, but some tend to be little discussed in a direct manner relevant to gas turbines. These include uniformity of internal cooling, ultimate film cooling, microcooling, reduced incident heat flux, secondary flows as prime cooling, contoured gas paths, thermal stress reduction, controlled cooling, low emission combustor-turbine systems, and regenerative cooling. Evolutionary or revolutionary advancements concerning these issues will ultimately be required in realizable engineering forms for gas turbines to breakthrough to new levels of performance. Herein lies the challenge to researchers and designers. It is the intention of this summary to provide a concise review of these issues, and some of the recent solution directions, as an initial guide and stimulation to further research.
    publisherThe American Society of Mechanical Engineers (ASME)
    titleGas Turbine Heat Transfer: Ten Remaining Hot Gas Path Challenges
    typeJournal Paper
    journal volume129
    journal issue2
    journal titleJournal of Turbomachinery
    identifier doi10.1115/1.2464142
    journal fristpage193
    journal lastpage201
    identifier eissn1528-8900
    keywordsCooling
    keywordsTurbines
    keywordsFlow (Dynamics)
    keywordsGas turbines
    keywordsDesign AND Heat transfer
    treeJournal of Turbomachinery:;2007:;volume( 129 ):;issue: 002
    contenttypeFulltext
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