Computational analysis of span-wise hole locations on fluid flow and film cooling of internal channels with crescent ribs

Zhang, Guohua; Liu, Xueting; Sundén, Bengt; Xie, Gongnan

doi:10.1108/hff-09-2018-0474

Cited by 2 publications

(1 citation statement)

References 39 publications

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“…Some research works about film cooling are fundamental studies which are performed on a flat plate and concentrate on one parameter by isolating the effects of other parameters (Natsui et al , 2017; Wang et al , 2019; Zhang et al , 2019; Hou et al , 2019). Natsui et al (Natsui et al , 2017) measured the adiabatic film cooling effectiveness ( ƞ ) on a flat surface with multi-row arrays of film cooling holes by pressure-sensitive paint (PSP) method.…”

Section: Introductionmentioning

confidence: 99%

Numerical investigations of endwall film cooling design of a turbine vane using four-holes pattern

Liu

et al. 2021

HFF

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Purpose Endwall film cooling protects vane endwall by coolant coverage, especially at the leading edge (LE) region and vane-pressure side (PS) junction region. Strong flow impingement and complex vortexaa structures on the vane endwall cause difficulties for coolant flows to cover properly. This work aims at a full-scale arrangement of film cooling holes on the endwall which improves coolant efficiency in the LE region and vane-PS junction region. Design/methodology/approach The endwall film holes are grouped in four-holes constructal patterns. Three ways of arranging the groups are studied: based on the pressure field, the streamlines or the heat transfer field. The computational analysis is done with the k-ω SST model after validating the turbulence model properly. Findings By clustering the film cooling holes in four-holes patterns, the ejection of the coolant flow is stronger. The four-holes constructal patterns also improve the local coolant coverage in the “tough” regions, such as the junction region of the PS and the endwall. The arrangement based on streamlines distribution can effectively improve the coolant coverage and the arrangement based on the heat transfer distribution (HTD) has benefits by reducing high-temperature regions on the endwall. Originality/value A full-scale endwall film cooling design is presented considering interactions of different film cooling holes. A comprehensive model validation and mesh independence study are provided. The cooling holes pattern on the endwall is designed as four-holes constructal patterns combined with several arrangement choices, i.e. by pressure, by heat transfer and by streamline distributions.

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Section: Introductionmentioning

confidence: 99%

Numerical investigations of endwall film cooling design of a turbine vane using four-holes pattern

Liu

et al. 2021

HFF

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Numerical analysis for film cooling characteristics of trenched hole under the effects of rib-disturbed feed flow and curved surface

Luo

Yan

et al. 2023

Physics of Fluids

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Film holes are extensively utilized to protect the blade external surface by ejecting coolant, forming a protective film, and separating the hot gas and blade surface. Trenched holes, caused by the turbine blade coated with thermal barrier, greatly feature better film cooling performance than traditional cylinder holes. In this study, the effects of a rib-disturbed feed flow on the film cooling performance of trenched holes are studied through the numerical method. Two typical rib attacking angles, 45° and 135°, are compared with the blowing ratio increasing from 0.5 to 2.0. The effects of the curved surface (convex and concave) are also included. Numerical results prove that film effectiveness with the coolant fed by the rib-disturbed internal flow is sensitive to the blowing ratio. The rib-turbulated cooling flow entering the film hole is featured with different swirling states; therefore, the interaction between the mainstream and the cooling air of varied swirling state leads to different film coverage and effectiveness. Overall, 135° ribs induce better adiabatic film cooling effectiveness than 45° ribs, with a maximum improvement 34.9% at M = 0.5. Film effectiveness on the convex surface is better than that on flat and concave surfaces. Area-averaged η on convex and concave surfaces is, respectively, 4.7% higher and 6.2% lower than that on the flat surface. Normal pressure gradient established on the convex surface contributes to reducing the turbulence intensity and improving the film lateral coverage.

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Computational analysis of span-wise hole locations on fluid flow and film cooling of internal channels with crescent ribs

Cited by 2 publications

References 39 publications

Numerical investigations of endwall film cooling design of a turbine vane using four-holes pattern

Numerical investigations of endwall film cooling design of a turbine vane using four-holes pattern

Numerical analysis for film cooling characteristics of trenched hole under the effects of rib-disturbed feed flow and curved surface

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