2018
DOI: 10.1016/j.applthermaleng.2017.09.008
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Influence of simplifications of blade in gas turbine on film cooling performance

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Cited by 35 publications
(7 citation statements)
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“…Figure 6 shows the spanwise single-row cooling effectiveness distribution. The adiabatic film cooling effectiveness was defined (Zeng et al, 2018). As the cooling hole row location reaches the shock reflection point, the direction of coolant ejection into the channel varies.…”
Section: The Effect Of Film Cooling Hole Positionmentioning
confidence: 99%
“…Figure 6 shows the spanwise single-row cooling effectiveness distribution. The adiabatic film cooling effectiveness was defined (Zeng et al, 2018). As the cooling hole row location reaches the shock reflection point, the direction of coolant ejection into the channel varies.…”
Section: The Effect Of Film Cooling Hole Positionmentioning
confidence: 99%
“…Modelos como este podem apresentar discordâncias em comparação com o caso real, gerando erros da ordem de 15%, segundo Incropera et al (2007). Entretanto, apesar dessas possíveis disparidades, o método é viável para os casos em que se realiza uma adaptação da geometria mantendo a mesma área superficial e as mesmas condições internas presentes no contorno da pá de geometria complexa, conforme se observa no trabalho de Zeng et al (2018).…”
Section: Metodologiaunclassified
“…Effective cooling of the end wall and turbine blade with a certain amount of secondary flow is the key to turbine blade thermal protection. 1,2,3 Internal swirl flow devices are widely used in the internal passage of blade, such as ribs and dimples, which have also been intensively studied. 4,5 In the turbine cascades, accurately predicting the position of transition in the boundary layer of the surface plays a decisive role in designing the heat transfer surfaces, for example, reduce the friction of blade surface, and control the heat transfer coefficient.…”
Section: Introductionmentioning
confidence: 99%