Aerothermal effects of squealer openings on a cavity tip in a turbine cascade
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Zuhao Liu
und
Zhiyuan Cao
Abstract
Both the aerodynamic and thermal performance are important for a high-pressure turbine design. This paper investigates aerothermal effects of opening on the suction side squealer of a cavity tip in a turbine cascade. There are four cases investigated, ‘Cavity’, ‘Opening 1’, ‘Opening 2’ and ‘Opening 3’. For Opening 1 with an opening area at 15 % axial chord, the opening outflow affects the near-tip flow mainly by interacting with the passage vortex, and the near tip loss increases by less than 3 %. For Opening 2 with an opening area at 12 % axial chord, the near tip loss is lower than Opening 1. By further rounding the edge of the opening area, the loss of the tip with opening is less than 1 % higher than the cavity tip. Nevertheless, the opening tip can achieve a reduction of the thermal load of the suction side squealer inner wall by up to 19 %.
Funding source: Natural Science Foundation of China (NSFC)
Award Identifier / Grant number: Grant No. 52076001
Funding source: National Science and Technology Major Project
Award Identifier / Grant number: 2019-Ⅱ-0011-0031
Funding source: Science and Technology Major Project of Jiangxi Province
Award Identifier / Grant number: 20203ABC28W002
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Research ethics: The authors understand that plagiarism and falsification of data are serious academic misconduct. The paper is written according to the research ethics.
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Author contributions: The authors have accepted responsibility for the entire content of this manuscript and approved its submission.
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Competing interests: The author(s) state(s) no conflict of interest.
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Research funding: This study was funded by Natural Science Foundation of China (NSFC), Grant No. 52076001; National Science and Technology Major Project (2019-Ⅱ-0011-0031); Science and Technology Major Project of Jiangxi Province (20203ABC28W002).
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Data availability: The raw data can be obtained on request from the corresponding author.
References
1. Palafox, P, Oldfield, ML, LaGraff, JE, Jones, TV. PIV maps of tip leakage and secondary flow fields on a low-speed turbine blade cascade with moving endwall. J Turbomach 2008;130:011001. https://doi.org/10.1115/1.2437218.Suche in Google Scholar
2. Bindon, JP. The measurement and formation of tip clearance loss. J Turbomach 1989;111:257–63. https://doi.org/10.1115/1.3262264.Suche in Google Scholar
3. Harvey, NW. Turbine blade tip design and tip clearance treatment. VKI LECTURE Series. Brussels: Von Karman Institute; 2004.Suche in Google Scholar
4. Denton, JD. Loss mechanisms in turbomachines. ASME 1993; Paper No: 93-GT-435, V002T14A001; 40 p. https://doi.org/10.1115/93-GT-435.Suche in Google Scholar
5. Rains, DA. Tip clearance flows in axial compressors and pumps [Doctoral dissertation]. California Institute of Technology; 1954.10.21236/AD0037339Suche in Google Scholar
6. Heyes, FJ, Hodson, HP, Dailey, GM. The effect of blade tip geometry on the tip leakage flow in axial turbine cascades. J Turbomach 1992;114:643–51. https://doi.org/10.1115/1.2929188.Suche in Google Scholar
7. Key, N, Arts, T. Comparison of turbine tip leakage flow for flat tip and squealer tip geometries at high-speed conditions. J Turbomach 2006;128:213–20. https://doi.org/10.1115/1.2162183.Suche in Google Scholar
8. Krishnababu, SK, Newton, PJ, Dawes, WN, Lock, GD, Hodson, HP, Hannis, J, et al.. Aerothermal investigations of tip leakage flow in axial flow turbines—Part I: effect of tip geometry and tip clearance gap. J Turbomach 2009;131:011008. https://doi.org/10.1115/1.2950068.Suche in Google Scholar
9. Zhou, C, Hodson, HP. The tip leakage flow of an unshrouded high pressure turbine blade with tip cooling. J Turbomach 2011;133:041028. https://doi.org/10.1115/1.4001174.Suche in Google Scholar
10. Zhou, C, Hodson, H. Squealer geometry effects on aerothermal performance of tip-leakage flow of cavity tips. J Propul Power 2012;28:556–67. https://doi.org/10.2514/1.b34254.Suche in Google Scholar
11. He, XJ, Zou, ZP, Yao, LC, Fu, C. Refined flow organization in squealer tip gap and its impact on turbine aerodynamic performance. Aero Sci Technol 2023;138:108331. https://doi.org/10.1016/j.ast.2023.108331.Suche in Google Scholar
12. Bi, S, Mao, JK, Chen, PT, Han, F, Wang, L. Effect of multiple cavities and tip injection on the aerothermal characteristics of the squealer tip in turbine stage. Appl Therm Eng 2023;220:119631. https://doi.org/10.1016/j.applthermaleng.2022.119631.Suche in Google Scholar
13. Li, L, Jiang, DY, Zhou, C, Luo, H, Hou, W, Chang, Q. Near tip loss control with a Winglet Baffle cavity tip in a turbine cascade. J Eng Gas Turbines Power 2021;143:101007. https://doi.org/10.1115/1.4050632.Suche in Google Scholar
14. Wang, YB, Song, YP, Yu, JY, Chen, F. Effect of cooling injection on the leakage flow of a turbine cascade with honeycomb tip. Appl Therm Eng 2018;133:690–703. https://doi.org/10.1016/j.applthermaleng.2018.01.090.Suche in Google Scholar
15. Fu, YF, Chen, F, Liu, HP, Song, Y. Experimental and numerical study of honeycomb tip on suppressing tip leakage flow in turbine cascade. J Turbomach 2018;140:061006. https://doi.org/10.1115/1.4039049.Suche in Google Scholar
16. Kwak, JS, Ahn, J, Han, JC, Lee, CP, Bunker, RS, Boyle, R, et al.. Heat transfer coefficients on the squealer tip and near-tip regions of a gas turbine blade with single or double squealer. J Turbomach 2003;125:778–87. https://doi.org/10.1115/1.1626684.Suche in Google Scholar
17. Bunker, RS. Axial turbine blade tips: function, design, and durability. J Propul Power 2006;22:271–85. https://doi.org/10.2514/1.11818.Suche in Google Scholar
18. Azad, GS, Han, J-C, Bunker, RS, Lee, CP. Effect of squealer geometry arrangement on a gas turbine blade tip heat transfer. J Heat Tran 2002;124:452–9. https://doi.org/10.1115/1.1471523.Suche in Google Scholar
19. Hughes, WF, Gaylord, EW. Schaum’s theory and problem of basic equations of engineering. New York: McGraw-Hill; 1964.Suche in Google Scholar
20. Metzg, DE, Rue, K. The influence of turbine clearance gap leakage on passage velocity and heat transfer near blade tips: Part I—sink flow effects on blade pressure side. J Turbomach 1989;111:284–92. https://doi.org/10.1115/1.3262267.Suche in Google Scholar
© 2023 Walter de Gruyter GmbH, Berlin/Boston
Artikel in diesem Heft
- Frontmatter
- Proper Orthogonal Decomposition analysis of mode switching in supersonic jets impinging on flat and corrugated plates
- Impact of cavity and ramp configuration on the combustion performance of a strut-based scramjet combustor
- In-service load calculation surrogate models for high-pressure turbine blade life digital twin
- Numerical analysis on the effect of passive control geometry in supersonic jet mixing enhancement
- Study on one-dimensional performance prediction of multi-stage axial turbine based on the blade height
- Dynamic characteristics of open-ends squeeze film dampers with air ingestion
- Fluid flow in a microdiffuser at small Reynolds numbers
- A study on optimal rotor speed control method for helicopter power system considering the influence of infrared suppressors
- Effects of turbulence and flamelet combustion modelling on the CFD simulation of a dual inlet ramjet combustor
- Design and combustion characteristics analysis of a static shaft turbofan engine
- Aerothermal effects of squealer openings on a cavity tip in a turbine cascade
- Endwall heat transfer in wedge channel with teardrop pin fins, circular fins and oblong pin fins
- Virtual deflection with synthetic jet actuators at high angles of attack
- Design of mode transition control system for tandem TBCC engine based on direct performance parameters closed-loop control
- Effect of tab shape, length, and placement on the over-expanded free jet at Mach 2.0
- Influence of the ending position of controllable speed casing on a transonic compressor rotor tip leakage flow
- Integrated modeling and coupling characteristics analysis of helicopter/engine/infrared suppressor
- Effect of velocity ratio and Mach number on thin lip coaxial jet
- C conjugate heat transfer simulation of swirl internal cooling on blade leading edge
- Influence of inlet structure on combustion flow structure in magnesium powder fueled water ramjet engine
- Research on high-bandwidth linear active disturbance rejection control method for variable speed turboshaft engine
- Numerical investigation of force over the horizontal jet tab of various sector angle fixed to the convergent-divergent nozzle exit
Artikel in diesem Heft
- Frontmatter
- Proper Orthogonal Decomposition analysis of mode switching in supersonic jets impinging on flat and corrugated plates
- Impact of cavity and ramp configuration on the combustion performance of a strut-based scramjet combustor
- In-service load calculation surrogate models for high-pressure turbine blade life digital twin
- Numerical analysis on the effect of passive control geometry in supersonic jet mixing enhancement
- Study on one-dimensional performance prediction of multi-stage axial turbine based on the blade height
- Dynamic characteristics of open-ends squeeze film dampers with air ingestion
- Fluid flow in a microdiffuser at small Reynolds numbers
- A study on optimal rotor speed control method for helicopter power system considering the influence of infrared suppressors
- Effects of turbulence and flamelet combustion modelling on the CFD simulation of a dual inlet ramjet combustor
- Design and combustion characteristics analysis of a static shaft turbofan engine
- Aerothermal effects of squealer openings on a cavity tip in a turbine cascade
- Endwall heat transfer in wedge channel with teardrop pin fins, circular fins and oblong pin fins
- Virtual deflection with synthetic jet actuators at high angles of attack
- Design of mode transition control system for tandem TBCC engine based on direct performance parameters closed-loop control
- Effect of tab shape, length, and placement on the over-expanded free jet at Mach 2.0
- Influence of the ending position of controllable speed casing on a transonic compressor rotor tip leakage flow
- Integrated modeling and coupling characteristics analysis of helicopter/engine/infrared suppressor
- Effect of velocity ratio and Mach number on thin lip coaxial jet
- C conjugate heat transfer simulation of swirl internal cooling on blade leading edge
- Influence of inlet structure on combustion flow structure in magnesium powder fueled water ramjet engine
- Research on high-bandwidth linear active disturbance rejection control method for variable speed turboshaft engine
- Numerical investigation of force over the horizontal jet tab of various sector angle fixed to the convergent-divergent nozzle exit
