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Superposition effect of the laidback fan-shaped film cooling hole on a gas turbine vane

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Abstract

The superposition effect of optimized laidback fan-shaped film cooling holes on a vane was experimentally investigated. The film cooling experiments were conducted using a linear cascade with five vanes and the blow-down cascade facility of the Korea Aerospace University. The Reynolds number calculated using the velocity of cascade exit and chord length of vane was 1.1×106. The film cooling effectiveness (FCE) was investigated by applying a pressure sensitive paint technique with a density ratio of 1.5 (DR) and four different blowing ratios (BR). To focus the superposition of the coolant, each coolant cavity had only a single-row holes and the flow rate for each cavity was separately controlled. Also, test vanes were designed so that the flow disturbance by the upstream non-injecting holes was excluded. The dimensions of the laidback fan-shaped (LBF) hole installed on the vane was derived from a series of experimental optimization processes using a flat plate test section at the DR of 1.5 and BR of 2.0 conditions. The cascade test results presented that FCE of the optimized LBF hole increased as the BR increased and FCE of suction side (SS) showed superior film cooling performance compared to the pressure side (PS). Generally, the FCE obtained by superposing the single-row injection case was well-matched with FCE of multi-row injection cases. The difference between the two results enlarged toward downstream, however, the maximum difference was only 0.03 units.

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Abbreviations

AR :

Area ratio of outlet to inlet [Aoutlet/Ainlet]

C :

Chord length of vane [mm]

D :

Diameter of hole [mm]

DR :

Density ratio of coolant to mainstream

I :

Intensity

L :

Length of hole [mm]

M :

Blowing ratio

x :

Axial distance [mm]

α :

Injection angle [°]

β :

Forward expansion angle [°]

γ :

Lateral expansion angle [°]

η :

Film cooling effectiveness

ω :

Molecular weight

air :

Air injection condition

blk :

Black condition

c :

Coolant

fg :

Foreign gas injection condition

fwd :

Forward expansion angle

h :

Hole row location

i, j :

Row number

O 2 :

Oxygen

ref :

Reference condition

s :

Superposition

LE :

Leading edge

TE :

Leading edge

SS :

Suction side

PS :

Reference condition

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Acknowledgments

This work was partly supported by Korea Institute of Energy Technology Evaluation and Planning (KETEP) grant funded by the Korea government (MOTIE) (Grant No. 20193310100050) and Basic Science Research Program through the National Research Foundation of Korea (NRF) funded by the Ministry of Education (Grant No. 2022R1A6A1A03056784).

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Authors and Affiliations

  1. School of Mechanical and Aerospace Engineering, Korea Aerospace University, Goyang, 10540, Korea

    Ye Rim Jo, Jin Young Jeong, Min Seok Kang, Woojun Kim & Jae Su Kwak

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  1. Ye Rim Jo
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  2. Jin Young Jeong
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  3. Min Seok Kang
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  5. Jae Su Kwak
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Corresponding author

Correspondence to Jae Su Kwak.

Additional information

Ye Rim Jo is currently working on her master’s degree from the School of Aerospace and Mechanical Engineering in the Korea Aerospace University, Goyang, Korea. Her research interests include optimization of film cooling hole in the gas turbine.

Jin Young Jeong is currently working on his doctoral degree from the School of Aerospace and Mechanical Engineering in the Korea Aerospace University, Goyang, Korea. He received his Master’s degree in Heat and Fluid Engineering from Korea Aerospace University. His research interests include heat transfer and cooling technology in the gas turbine.

Min Seok Kang received his Master’s degree in Heat and Fluid Engineering from Korea Aerospace University. His research interests include film cooling technique in the gas turbine.

Woojun Kim is currently working on his doctoral degree from the School of Aerospace and Mechanical Engineering in the Korea Aerospace University, Goyang, Korea. He received his Master’s degree in Heat and Fluid Engineering from Korea Aerospace University. His research interests include heat transfer measurement technique in the gas turbine.

Jae Su Kwak is a Professor of the School of Aerospace and Mechanical Engineering in the Korea Aerospace University, Goyang, Korea. He received his Ph.D. degree in Mechanical Engineering from Texas A&M University, College Station, United States. His research interests include aerodynamics and heat transfer in the gas turbine.

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Jo, Y.R., Jeong, J.Y., Kang, M.S. et al. Superposition effect of the laidback fan-shaped film cooling hole on a gas turbine vane. J Mech Sci Technol 37, 5449–5461 (2023). https://doi.org/10.1007/s12206-023-0944-1

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  • DOI: https://doi.org/10.1007/s12206-023-0944-1

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