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contributor authorWang, Huihui
contributor authorDeng, Qinghua
contributor authorHe, Wei
contributor authorFeng, Zhenping
date accessioned2023-08-16T18:10:58Z
date available2023-08-16T18:10:58Z
date copyright1/9/2023 12:00:00 AM
date issued2023
identifier issn0889-504X
identifier otherturbo_145_6_061009.pdf
identifier urihttp://yetl.yabesh.ir/yetl1/handle/yetl/4291571
description abstractEfficient cooling is imperative for gas turbine blades that suffer from hot gas erosion. Cooling and flow characteristics of multi-channel wall jet structure combined with film holes for blade leading edge are numerically investigated through the Reynolds-averaged Navier–Stokes method in this paper. Several geometrical schemes with different rows and diameters of film holes were conducted, and the influences of the cooling air mass flow ratio of the first coolant supply cavity were also considered, which presented the detailed flow and cooling characteristics of wall jet and film composite cooling on conjugate heat transfer. The results implied that film extraction improves the overall cooling effectiveness compared with pure wall jet cooling. And the mainstream intrusion happens in some film holes at the bottom of blades, especially on the pressure side. The film-hole diameter can raise the mass flow ratio and enhance external thermal protection produced by cooling air, and it also affects the uniformity of film flow and the temperature gradient of some regions for turbine blades. Furthermore, the cooling performance and pressure loss are significantly influenced by the coolant mass flowrate of the first cooling air supply cavity. This study will offer a consultation for the design of film-hole structures for multi-channel wall jet cooling.
publisherThe American Society of Mechanical Engineers (ASME)
titleCooling and Flow Characteristics of Multi-Channel Wall Jet Structure With Film Holes at Blade Leading Edge
typeJournal Paper
journal volume145
journal issue6
journal titleJournal of Turbomachinery
identifier doi10.1115/1.4056513
journal fristpage61009-1
journal lastpage61009-12
page12
treeJournal of Turbomachinery:;2023:;volume( 145 ):;issue: 006
contenttypeFulltext


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