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Full Length Article | Open Access

Control of squealer-tip leakage flow with perforated-rib coolant injection in an axial turbine cascade

Shengchang ZHANGa, Qinqin WANGb,c, Xiaoming TANa,( ), Jingzhou ZHANGa
College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China
School of Energy and Power Engineering, Beihang University, Beijing 100191, China
AECC Sichuan Gas Turbine Research Establishment, Chengdu 610500, China

Peer review under responsibility of Editorial Committee of CJA.

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Abstract

A novel perforated-rib configuration is proposed for controlling the tip leakage flow at the rotor tip of an axial turbine. Three perforated-rib layouts are considered, wherein a perforated rib is installed at (A) the Suction-Side squealer (SS-rib), (B) the Pressure-Side squealer (PS-rib), and (C) the additional squealer along the blade Camber Line (CL-rib). A numerical method is used to show how the novel rib layouts affect the aerodynamic performance of the tip leakage flow. Results show that the coolant jets issuing from the perforated-rib injection holes penetrate deeper into the tip clearance than those in the baseline squealer-tip case, and how the perforated-rib coolant injection affects the tip leakage flow depends strongly on the rib layout. The PS-rib and CL-rib layouts appear promising for controlling the tip leakage flow, playing a significant role in reducing the total pressure loss and improving the turbine blade’s isentropic efficiency. In particular, under an injection mass flow ratio of 1% and a tip clearance of 1% blade span, the PS-rib layout reduces the leakage mass flow rate by 27% and increases the isentropic efficiency by 1.25% compared with those in the baseline squealer-tip case. Meanwhile, the advantages of the PS-rib layout in tip leakage control are confirmed under small and large tip clearances.

Keywords

AerodynamicsTip leakage flowPerforated ribSquealer tipTip injection

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Chinese Journal of Aeronautics
Volume 36 Issue 8,
August 2023
Pages 54-73
DOI: 10.1016/j.cja.2023.04.015
Cite this article:
ZHANG S, WANG Q, TAN X, et al. Control of squealer-tip leakage flow with perforated-rib coolant injection in an axial turbine cascade. Chinese Journal of Aeronautics, 2023, 36(8): 54-73. https://doi.org/10.1016/j.cja.2023.04.015

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Received: 04 July 2022
Revised: 31 July 2022
Accepted: 19 September 2022
Published: 17 April 2023
© 2023 Chinese Society of Aeronautics and Astronautics.

This is an open access article under the CC BY-NC-ND license (http://creativecommons.org/licenses/by-nc-nd/4.0/).
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