Study on Heat Transfer Characteristics of Jet Impingement of Turbine Bending Surface

The architecture of aeroengine air-cooling system channels is notably intricate, with impingement heat transfer standing out as a critical process amidst the complexity. This study delves into the casing annular cavity’s structure, examining the influence of flow and structural parameters on heat tr...

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Bibliographic Details
Published inAerospace Vol. 11; no. 7; p. 554
Main Authors Zeng, Fei, Sun, Ruijia, Chen, Zhenhua, Liu, Yuang, Yang, Weihua
Format Journal Article
LanguageEnglish
Published Basel MDPI AG 01.07.2024
Subjects
Cooling
Cooling systems
Cross flow
crossflow ratio
Efficiency
Fluid flow
Heat transfer
Heat transfer coefficients
hole consistency
impingement angle
impingement distance
Investigations
Jet impingement
Reynolds number
Simulation
Stagnation point
Temperature distribution
turbine casing
Turbines
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Summary:The architecture of aeroengine air-cooling system channels is notably intricate, with impingement heat transfer standing out as a critical process amidst the complexity. This study delves into the casing annular cavity’s structure, examining the influence of flow and structural parameters on heat transfer characteristics. Experimental findings have revealed a trend towards more uniform temperature distributions across the impingement target plate as the relative impingement distance (H/d) increases, under a constant impingement Reynolds number (Rej). Notably, an impingement angle (β) of 90° yields optimal heat transfer effects on the target surface. Furthermore, a higher impingement hole consistency (Is) correlates with a lower and more uniform temperature distribution across the target plate. Additionally, escalating the crossflow ratio (mc/m) results in a decline in the temperature at the impingement stagnation point and a corresponding rise in the heat transfer coefficient.
ISSN:2226-4310
2226-4310
DOI:10.3390/aerospace11070554