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Conjugated heat transfer characteristics of ribbed-swirl cooling in turbine blade under rotation condition

  • Kun Xiao , Xiandi Zhao , Juan He , Zhaokai Ma EMAIL logo and Zhenping Feng
Published/Copyright: November 25, 2024
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International Journal of Turbo & Jet-Engines
From the journal International Journal of Turbo & Jet-Engines Volume 42 Issue 2

Abstract

Ribbed-swirl cooling performs excellently in enhancing heat transfer, but previous studies were almost conducted in simple circular tubes under static conditions. The influence of actual mainstream flow, heat conduction of blade as well as the rotation effect was ignored. To explore its application potential in a real environment, the thermal performance of swirling cooling after adding annular ribs to its target surface in a real turbine blade was analyzed, and the impacts of centrifugal force along with Coriolis force were also included. From the results, the ribs affected the distribution of nozzle mass flow rate. For nozzles near the blade root, the mass flow rates in ribbed-swirl cooling were smaller than those in smooth-swirl chamber, while near blade tip, those were higher. Besides, the influence of Coriolis force from SS (suction side) to PS (pressure side) on the development of cross-flow and swirl in smooth and ribbed chamber exerted a significant difference. For ribbed-swirl cooling, cross-flow passing through ribs induced flow separation, which was conducted to cross-flow suppression. The combined action of the above two aspects led to an obvious heat transfer advantage of ribbed-swirl cooling. In comparison to smooth-swirl chamber, its blade surface temperature was further reduced to more than 25 K.

Keywords: turbine blade; heat transfer; swirl cooling; cross-flow
Corresponding author: Zhaokai Ma, Ministry of Industry and Information Technology Key Laboratory of Thermal Management and Energy Utilization of Aviation Vehicles, College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China, E-mail:

Acknowledgments

The authors would like to acknowledge the financial support from Ministry of Industry and Information Technology Key Laboratory of Thermal Management and Energy Utilization of Aviation Vehicles and Jiangsu Province Provincial department of science and technology (No. BK20241413).

  1. Research ethics: Not applicable.

  2. Informed consent: Not applicable.

  3. Author contributions: All authors have accepted responsibility for the entire content of this manuscript and approved its submission. Kun Xiao: Conceptualization, Data Curation, Formal Analysis, Investigation, Writing – Original Draft, Xiandi Zhao: Methodology, Juan He: Investigation, Writing – Review & Editing, Zhaokai Ma: Funding Acquisition, Writing – Review & Editing, Zhenping Feng: Project Administration.

  4. Use of Large Language Models, AI and Machine Learning Tools: None declared.

  5. Conflict of interest: The author states no conflict of interest.

  6. Research funding: Ministry of Industry and Information Technology Key Laboratory of Thermal Management and Energy Utilization of Aviation Vehicles(No.CEPE2024005), Jiangsu Province Provincial department of science and technology (No. BK20241413).

  7. Data availability: All data generated or analyzed during this study are included in this published article.

Nomenclature

Symbols

Fi

Body force, N

f

Friction factor

H

Height of the jet nozzles, mm

h

Heat transfer coefficient, W/(m2·K)

h r

Height of ribs, mm

L

Length of the swirl chamber, mm

Nu

Nusselt number

N 0

Total internal energy, J

P

Pressure, kPa

PS

Pressure surface

q

Heat flux, W/m2

Re

Reynolds number

S

Area, m2

SS

Suction surface

S ij

Strain rate tensor

T

Temperature, K

t

Time, s

U

Velocity, m/s

W

Width of the jet nozzles, mm

Greek symbols

ρ

Density of gas, kg/m3

μ

Dynamic viscosity, m2/s

λ

Thermal conductively, W/(m·K)

σ ij

Stress tensor

Subscripts

a

Area-averaged

cir

Circumferentially-averaged

In

Inlet

w

Wall

0

Baseline

References

1. Han, JC, Dutta, S, Ekkad, S. Gas turbine heat transfer and cooling technology, 2nd ed Boca Raton: Taylor and Francis; 2012.10.1201/b13616Search in Google Scholar

2. Liu, Z, Feng, ZP. Numerical simulation on the effect of jet nozzle position on impingement cooling of gas turbine blade leading-edge. Int J Heat Mass Tran 2011;54:4949–59. https://doi.org/10.1016/j.ijheatmasstransfer.2011.07.008.Search in Google Scholar

3. Wang, N, Chen, AF, Zhang, MJ, Han, JC. Turbine blade leading-edge cooling with one row of normal or tangential impinging jets. ASME J. Heat Transf. 2018;140:062201. https://doi.org/10.1115/1.4038691.Search in Google Scholar

4. Wang, N, Han, JC. Swirl impinging cooling on an airfoil leading-edge model at large Reynolds number. ASME J Therm Sci Eng Appl 2019;11:031006. https://doi.org/10.1115/1.4042151.Search in Google Scholar

5. Zhang, MJ, Wang, N, Han, JC. Internal heat transfer of film-coolant leading-edge model with normal and tangential impinging jets. Int J Heat Mass Tran 2019;139:193–204. https://doi.org/10.1016/j.ijheatmasstransfer.2019.04.140.Search in Google Scholar

6. Zhang, MJ, Wang, N, Han, JC. Overall effectiveness of film-coolant leading-edge model with normal and tangential impinging jets. Int J Heat Mass Tran 2019;139:577–87. https://doi.org/10.1016/j.ijheatmasstransfer.2019.05.037.Search in Google Scholar

7. Fan, XJ, Li, L, Zou, JS, Zhou, YY. Cooling methods for gas turbine blade leading-edge: comparative study on impingement cooling, swirl cooling and double swirl cooling. Int Commun Heat Mass Tran 2019;100:133–45. https://doi.org/10.1016/j.icheatmasstransfer.2018.12.017.Search in Google Scholar

8. Kreith, F, Margolis, D. Heat transfer and friction in turbulent vortex flow. Appl Sci Res 1959;8:457–73. https://doi.org/10.1007/bf00411769.Search in Google Scholar

9. Hay, N, West, PD. Heat transfer in free swirling flow in a pipe. ASME J Heat Transf 1975;97:411–16. https://doi.org/10.1115/1.3450390.Search in Google Scholar

10. Tu, JP, Gu, WZ, Shen, JR, Liu, WY. An investigation of the swirling flow and heat transfer in a duct. J Therm Sci 1992;1:19–23. https://doi.org/10.1007/bf02650802.Search in Google Scholar

11. Chang, F, Dhir, VK. Turbulent flow field in tangentially injected swirl flows in tubes. Int J Heat Fluid Flow 1994;15:346–56. https://doi.org/10.1016/0142-727x(94)90048-5.Search in Google Scholar

12. Li, H, Tomita, Y. Characteristics of swirling flow in a circular pipe. ASME J Fluids Eng 1994;116:370–3. https://doi.org/10.1115/1.2910283.Search in Google Scholar

13. Ligrani, PM, Hedlund, CR, Babinchak, BT, Thambu, R, Moon, HK, Glezer, B. Flow phenomena in swirl chambers. Exp Fluid 1998;24:254–64. https://doi.org/10.1007/s003480050172.Search in Google Scholar

14. Hedlund, CR, Ligrani, PM, Moon, HK, Glezer, B. Heat transfer and flow phenomena in a swirl chamber simulating turbine blade internal cooling. ASME J Turbomach 1999;121:803–13.10.1115/1.2836734Search in Google Scholar

15. Hedlund, CR, Ligrani, PM, Glezer, B, Moon, HK. Heat transfer in a swirl chamber at different temperature ratios and Reynolds numbers. Int J Heat Mass Tran 1999;42:4081–91. https://doi.org/10.1016/s0017-9310(99)00086-1.Search in Google Scholar

16. Hedlund, CR, Ligrani, PM. Local swirl chamber heat transfer and flow structure at different Reynolds numbers. ASME J Turbomach 2000;122:375–85. https://doi.org/10.1115/1.555458.Search in Google Scholar

17. Thambu, R, Babinchak, BT, Ligrani, PM, Hedlund, CR, Moon, HK, Glezer, B. Flow in a simple swirl chamber with and without controlled inlet forcing. Exp Fluid 1999;26:347–57. https://doi.org/10.1007/s003480050298.Search in Google Scholar

18. Xiong, AK, Wei, QD. The decay of swirling flows in a type of cross-section-varying pipes. Appl Math Mech-Engl Ed 2001;22:983–8. https://doi.org/10.1007/bf02436398.Search in Google Scholar

19. Ling, JPCW, Ireland, PT, Harvey, NW. Measurement of heat transfer coefficient distributions and flow field in a model of a turbine blade cooling passage with tangential injection, presented at the ASME Turbo Expo 2006: turbomachinery Technical Conference and Exposition, No.GT200690352. Barcelona, Spain: American Society of Mechanical Engineers; 2006.10.1115/GT2006-90352Search in Google Scholar

20. Liu, Z, Feng, ZP, Song, LM. Numerical study on flow and heat transfer characteristics of swirl cooling on leading edge model of gas turbine blade, presented at the ASME Turbo Expo 2011: turbomachinery Technical Conference and Exposition, No.GT2011-46125. Vancouver, British Columbia, Canada: American Society of Mechanical Engineers; 2011.Search in Google Scholar

21. Liu, Z, Li, J, Feng, ZP. Numerical study of swirl cooling in a turbine blade leading-edge model. J Thermophys Heat Tran 2015;29:166–78. https://doi.org/10.2514/1.t4362.Search in Google Scholar

22. Liu, Z, Li, J, Feng, ZP, Simon, T. Numerical study on the effect of jet nozzle aspect ratio and jet angle on swirl cooling in a model of a turbine blade leading edge cooling passage. Int J Heat Mass Tran 2015;90:986–1000. https://doi.org/10.1016/j.ijheatmasstransfer.2015.07.050.Search in Google Scholar

23. Liu, Z, Li, J, Feng, ZP, Terrence, S. Numerical study on the effect of jet spacing on the swirl flow and heat transfer in the turbine airfoil leading edge region. Numer Heat Tranf A-Appl 2016;70:9806–994. https://doi.org/10.1080/10407782.2016.1230381.Search in Google Scholar

24. Du, CH, Li, L, Chen, XX, Fan, XJ, Feng, ZP. Numerical study on effects of jet nozzle angle and number on vortex cooling behavior for gas turbine blade leading edge, presented at the ASME Turbo Expo 2016: turbomachinery Technical Conference and Exposition, No.GT2016-57390. Seoul, South Korea: American Society of Mechanical Engineers; 2016.10.1115/GT2016-57390Search in Google Scholar

25. Du, CH, Li, L, Wu, X, Feng, ZP. Effect of jet nozzle geometry on flow and heat transfer performance of vortex cooling for gas turbine blade leading edge. Appl Therm Eng 2016;93:1020–32. https://doi.org/10.1016/j.applthermaleng.2015.09.087.Search in Google Scholar

26. Du, CH, Li, L, Li, S, Feng, ZP. Effects of aerodynamic parameters on steam vortex cooling behavior for gas turbine blade leading edge. Proc Inst Mech Eng Part A-J Power Energy 2016;230:1020–32. https://doi.org/10.1177/0957650916636974.Search in Google Scholar

27. Du, CH, Li, L, Fan, XJ. Numerical study on vortex cooling flow and heat transfer behavior under rotating conditions. Int J Heat Mass Tran 2017;105:638–47. https://doi.org/10.1016/j.ijheatmasstransfer.2016.10.028.Search in Google Scholar

28. Du, CH, Li, L, Fan, XJ, Feng, ZP. Rotational influences on aerodynamic and heat transfer behavior of gas turbine blade vortex cooling with bleed holes. Appl Therm Eng 2017;121:302–13. https://doi.org/10.1016/j.applthermaleng.2017.04.026.Search in Google Scholar

29. Biegger, C, Weigand, B. Flow and heat transfer measurements in a swirl chamber with different outlet geometries. Exp Fluid 2015;56:78. https://doi.org/10.1007/s00348-015-1937-3.Search in Google Scholar

30. Rao, Y, Biegger, C, Weigand, B. Heat transfer and pressure loss in swirl tubes with one and multiple tangential jets pertinent to gas turbine internal cooling. Int J Heat Mass Tran 2017;106:1356–67. https://doi.org/10.1016/j.ijheatmasstransfer.2016.10.119.Search in Google Scholar

31. Mohammad, DM, Mousavi, SM, Safikhani, H. Pareto optimal design of swirl cooling chambers with tangential injection using CFD, GMDH-type of ANN and NSGA-ii algorithm. Int J Therm Sci 2017;122:102–14. https://doi.org/10.1016/j.ijthermalsci.2017.08.016.Search in Google Scholar

32. Mousavi, SM, Ghadimi, B, Kowsary, F. Numerical study on the effects of multiple inlet slot configurations on swirl cooling of a gas turbine blade leading edge. Int Commun Heat Mass Tran 2018;90:34–43. https://doi.org/10.1016/j.icheatmasstransfer.2017.10.012.Search in Google Scholar

33. Wang, J, Liu, J, Wang, L, Sundén, B, Wang, ST. Conjugated heat transfer investigation with racetrack-shaped jet hole and double swirling chamber in rotating jet impingement. Numer Heat Tranf A-Appl 2018;73:768–87. https://doi.org/10.1080/10407782.2018.1454753.Search in Google Scholar

34. Fan, X, Xue, Y. Numerical investigation of nozzle geometry influence on the vortex cooling in an actual gas turbine blade leading edge cooling system. Heat Mass Tran 2022;58:575–86. https://doi.org/10.1007/s00231-021-03131-9.Search in Google Scholar

35. Wang, J, Li, L, Li, J, Wu, F, Du, CH. Numerical investigation on flow and heat transfer characteristics of vortex cooling in an actual film-cooled leading edge. Appl Therm Eng 2012;185:115942. https://doi.org/10.1016/j.applthermaleng.2020.115942.Search in Google Scholar

36. Glezer, B, Moon, HK, Kerrebrock, J, Bons, J, Guenette, G. Heat transfer in a rotating radial channel with swirling internal flow, presented at the ASME Turbo Expo 1998: turbomachinery Technical Conference and Exposition, No. GT-214. New York: American Society of Mechanical Engineers; 1998.10.1115/98-GT-214Search in Google Scholar

37. Fan, XJ, Li, L, Zou, JS, Wang, JF, Wu, F. Local heat transfer of swirl cooling with multiple tangential nozzles in a gas turbine blade leading-edge cooling passage. Int J Heat Mass Tran 2018;126:377–89. https://doi.org/10.1016/j.ijheatmasstransfer.2018.06.018.Search in Google Scholar

38. Fan, XJ, He, CX, Gan, L, Li, L, Du, CH. Experimental study of swirling flow characteristics in a semi cylinder swirl cooling configuration. Exp Therm Fluid Sci 2020;113:110036. https://doi.org/10.1016/j.expthermflusci.2019.110036.Search in Google Scholar

39. Liu, YY, Rao, Y, Weigand, B. Heat transfer and pressure loss characteristics in a swirl cooling tube with dimples on the tube inner surface. Int J Heat Mass Tran 2019;128:54–65. https://doi.org/10.1016/j.ijheatmasstransfer.2018.08.097.Search in Google Scholar

40. Xiao, K, He, J, Zheng, PF, Feng, ZP. Effects of circumferential ribs on suppressing cross-flow and enhancing heat transfer in swirl cooling. Int J Therm Sci 2022;181:107785. https://doi.org/10.1016/j.ijthermalsci.2022.107785.Search in Google Scholar

41. Xiao, K, He, J, Feng, ZP. Effects of variable jet nozzle angles on cross-flow suppression and heat transfer enhancement of swirl chamber. J Therm Sci 2022;31:214–23. https://doi.org/10.1007/s11630-022-1550-8.Search in Google Scholar

42. Xiao, K, He, J, Feng, ZP. Effects of trapezoid swirl chamber on cross-flow suppression and heat transfer enhancement in turbine blade leading-edge swirl cooling. Heat Tran Res 2022;53:55–73. https://doi.org/10.1615/heattransres.2022041942.Search in Google Scholar

43. Xiao, K, He, J, Feng, ZP. Heat transfer enhancement of swirl cooling by different crossflow diverters, presented at the ASME Turbo Expo 2022: turbomachinery Technical Conference and Exposition, No.GT2022-82775. Rotterdam, The Netherlands: American Society of Mechanical Engineers; 2022.10.1115/GT2022-82775Search in Google Scholar

44. Brost, V, Ruprecht, A, Maihofer, M. Rotor/stator interactions in an axial turbine, a comparison of transient and steady state frozen rotor simulations, Institute for Fluids Mechanics Hydraulic Machinery. Germany: University of Stuttgart; 2003.Search in Google Scholar

45. Kiml, R, Magda, A, Mochizuki, S, Murata, A. Rib-induced secondary flow effects on local circumferential heat transfer distribution inside a circular rib-roughened tube. Int J Heat Mass Tran 2004;47:1403–12. https://doi.org/10.1016/j.ijheatmasstransfer.2003.09.026.Search in Google Scholar
Received: 2024-05-23
Accepted: 2024-10-13
Published Online: 2024-11-25
Published in Print: 2025-05-26

© 2024 Walter de Gruyter GmbH, Berlin/Boston

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https://doi.org/10.1515/tjj-2024-0046
Keywords for this article
turbine blade; heat transfer; swirl cooling; cross-flow

Articles in the same Issue

  1. Frontmatter
  2. Deep residual ensemble model for predicting remaining useful life of turbo fan engines
  3. Review of gliding arc plasma assisted ignition and combustion for gas turbine application
  4. Interaction effects between the rotor wake and hub leakage flow in a multi-stage cantilevered compressor
  5. Determination of the modern marine single shaft gas turbine rotor blades fatigue strength parameters
  6. Role of different cavity flame holders on the performance characteristics of supersonic combustor
  7. Thermal performance of teardrop pin fins and zig zag ribs in a wedge channel
  8. Investigation of varying tip clearance gap and operating conditions on the fulfilment of low-speed axial flow fan
  9. Upgraded one-dimensional code for the design of a micro gas turbine mixed flow compressor stage with various crossover diffuser configurations
  10. Performance evaluation of a scramjet engine utilizing varied cavity aft wall divergence with parallel injection in a reacting flow field
  11. Speed controller design for turboshaft engine using a high-fidelity AeroThermal model
  12. Multi-nozzle thrust matching control of STOVL engine
  13. Numerical analysis of brush seal hysteresis based on orthogonal test method
  14. Conjugated heat transfer characteristics of ribbed-swirl cooling in turbine blade under rotation condition
  15. Flow pattern formation due to the interdependency of multi-component interactions and their impact on the performance of turbine and exhaust duct of gas turbine
  16. Flight trajectory optimization study of a variable-cycle turbine-based combined cycle engine hypersonic vehicle based on airframe/engine integration
  17. Constant temperature line identification on prototype gas turbine combustor with multi-colour change coating
  18. Sensitivity analysis of aero-engine performance optimization control system and its hardware test verification
  19. Compensator based improved model predictive control for Aero-engine
  20. Ignition experimental study based on rotating gliding arc
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