Aerothermodynamics

A Comparative Study of Purge Flow Aero-Thermal Performance under Pre-Swirl and Rotational Conditions

  • GAO Hongyu ,
  • WANG Yutian ,
  • XU Renjie ,
  • XU Qingzong
Expand
  • 1. School of Energy and Power Engineering, University of Shanghai for Science and Technology, Shanghai 200093, China
    2. Institute of Engineering Thermophysics, Chinese Academy of Sciences, Beijing 100045, China

Online published: 2025-03-05

Supported by

This work is supported by the National Natural Science Foundation of China (Grant No. 52106064).

Copyright

Science Press, Institute of Engineering Thermophysics, CAS and Springer-Verlag GmbH Germany, part of Springer Nature 2025

Abstract

Investigating the interaction between purge flow and main flow in gas turbines is crucial for optimizing thermal management, and enhancing aerodynamic efficiency. Measuring the high-speed rotating rotor poses challenges; however, employing the pre-swirl method to model rotational effect can facilitate experimental measurements. This study evaluates the validity of the pre-swirl method for modeling rotational effects. Numerical simulations are conducted under both stationary conditions, with seven swirl ratios, and rotational conditions. The investigation focuses on the underlying mechanisms of pre-swirl and rotation. Pre-swirl and rotation impart circumferential velocity to the purge flow relative to the blade, resulting in a diminishing effect on endwall cooling. On the other hand, pre-swirl reduces the adverse pressure gradient, and the rotation generates Coriolis forces acting on the passage vortex, both contribute to an increasing effect on endwall cooling. Under pre-swirl condition, the diminishing effect is dominant, while in rotational condition, neither the diminishing nor the increasing effect exhibits an overwhelmingly dominant trend.

Cite this article

GAO Hongyu , WANG Yutian , XU Renjie , XU Qingzong . A Comparative Study of Purge Flow Aero-Thermal Performance under Pre-Swirl and Rotational Conditions[J]. Journal of Thermal Science, 2025 , 34(2) : 626 -638 . DOI: 10.1007/s11630-025-2104-7

References

[1] Liu H., Qin J., Ji Z., et al., Study on the performance comparison of three configurations of aviation fuel cell gas turbine hybrid power generation system. Journal of Power Sources, 2021, 501: 230007.
[2] Dev N., Kumar R., Saha R. K., et al., Performance evaluation methodology for gas turbine power plants using graph theory and combinatorics. International Journal of Hydrogen Energy, 2024, 57: 1286–1301.
[3] Aygun H.J.E., Effects of air to fuel ratio on parameters of combustor used for gas turbine engines: Applications of turbojet, turbofan, turboprop and turboshaft. Energy, 2024, 305: 132346.
[4] Hai T., Alhaider M.M., Ghodratallah P., et al., Techno-economic-environmental study and artificial intelligence-assisted optimization of a multigeneration power plant based on a gas turbine cycle along with a hydrogen liquefaction unit. Applied Thermal Engineering, 2024, 237: 121660.
[5] Chen F., Zhang W., Cai J., et al., Design and optimization of a multi-level wasted heat recovery system for a natural gas-based gas turbine cycle; comprehensive exergy and economic analyses. Applied Thermal Engineering, 2024, 236: 121662.
[6] Okita Y., Kazawa J., Yamane T., et al., Aerodynamic impact of secondary air injection flowrates on the main annulus flow field for a transonic high-pressure turbine stage. Journal of Turbomachinery, 2024, 146(12): 121007.
[7] Farahani A.S., Kohandel H., Moradtabrizi H., et al., Power generation gas turbine performance enhancement in hot ambient temperature conditions through axial compressor design optimization. Applied Thermal Engineering, 2024, 236: 121733.
[8] Huang M., Zhang K., Li Z., et al., Aerothermal performance robustness and reliability analysis of turbine blade squealer tip with film cooling. Journal of Turbomachinery, 2024, 146(11): 111011.
[9] Li Y., Zhang H., Yin Z., et al., Investigation of unsteady flow in the unscalloped radial turbine cavity. Aerospace Science and Technology, 2021, 113: 106675.
[10] Gong W., Liu G., Chen K., et al., General method and application for evaluating system performance and sealing effectiveness of turbine rim seal flow and mainstream at large temperature difference. International Journal of Thermal Sciences, 2023, 193: 108438.
[11] Choi S., Bang M., Choi S.M., et al., Unsteady hot gas ingestion through the double rim-seals of an axial gas turbine. International Journal of Mechanical Sciences, 2021, 207: 106664.
[12] Meinke M., Schröder W.J., Analysis of single-blade passage and full circumference large-eddy simulations of turbine rim seal flows. Journal of Turbomachinery, 2024, 146: 041002.
[13] Mansouri Z.J.P., Aerodynamic and heat transfer performances of a highly loaded transonic turbine rotor with upstream generic rim seal cavity. Propulsion and Power Research, 2021, 10(4): 317–331.
[14] Sharmila P.P., Chatterjee D., Steady-state analysis of purge flow passage on the performance of the high-pressure transonic axial turbine at different mass flow ratios. Sādhanā, 2024, 49(1): 59. 
[15] Zhang Z., Zhang Y., Zhang Y., et al., Numerical investigation of the purge flow mechanisms and heat-transfer characteristics of turbine rim seals. Chinese Society for Industrial Technology Engineering, 2022, 40: 102484.
[16] Gao H., Dong Y., Li X., et al., Parameter sensitivity analysis of the interaction between purge flow and mainstream. Applied Thermal Engineering, 2024, 243: 122467.
[17] Feng M., Dai X., Zhang F., et al., Numerical investigation on film cooling and aerodynamic performance for gas turbine endwalls with upstream vane-type and cascade-type slots. Aerospace Science and Technology, 2024, 145: 108857.
[18] Qin R., Zhou X., Wang S., Cai L., Heat transfer and flow structure of a turbine blade’s air-cooled leading edge considering different hole shapes and additional flow angles. Journal of Thermal Science, 2024, 33(4): 1421–1442.
[19] Zhang K., Li Z., Huang M., et al., Uncertainty quantification of turbine endwall aero-thermal performance under combustor-turbine interface louver coolant and cavity. Applied Thermal Engineering, 2024, 253: 123800.
[20] Tang H., Scobie J.A., Wang Z., et al., A theoretical model for ingress through turbine rim seals based on physically-observed unsteadiness. International Journal of Heat and Fluid Flow, 2024, 106: 109300.
[21] Song L., Zhu P., Li J., et al., Effect of purge flow on endwall flow and heat transfer characteristics of a gas turbine blade. Applied Thermal Engineering, 2017, 110: 504–520.
[22] Kim G.M., Jeong J.Y., Kang Y.J., et al., A comparative study of purge slot exit shape on the film cooling effectiveness of a gas turbine shroud. International Journal of Thermal Sciences, 2024, 197: 108762.
[23] Zhang Z., Zhang Y., Xu D., et al., Flow mechanism between purge flow and mainstream in different turbine rim seal configurations. Chinese Journal of Aerospace, 2020, 33(8): 2162–2175.
[24] Sedani C., Panchal M., Chaudhuri P., Simulation and experimental analysis of purge gas flow characteristic for pebble bed. Fusion Engineering and Design, 2021, 172: 112778.
[25] Sedani C., Chaudhuri P., Gupta M.K., Heat transfer and fluid flow analysis of pebble bed and its verification with artificial neural network. Nuclear Materials and Energy, 2023, 35: 101439.
[26] Sedani C., Panchal M., Tanna V., Chaudhuri P., Gupta M.K., Analysis of effective thermal conductivity of pebble bed by artificial neural network and its computational and experimental verification. Case Studies in Thermal Engineering, 2022, 40: 102548.
[27] Hahn M., Schmid J., Bauer H., et al., Numerical investigation of heat transfer and purge flow mechanisms in a turbine cascade with bottom platform cavity. Propulsion and Power Systems, 2024, 15(3): 81–83.
[28] Tang R., Li H., Zhou Z., et al., Numerical investigation on the effect of sealing clearance on endwall film cooling effectiveness under rotating condition. Applied Thermal Engineering, 2024, 244: 122693.
[29] Patinios M., Scobie J.A., Sangan C.M., et al., Performance of rim-seals in upstream and downstream cavities over a range of flow coefficients. International Journal of Turbomachinery, Propulsion and Power, 2017, 2(4): 21.
[30] Park S., Tao Z., Guo Z., et al., Film cooling characteristics on blade platform with a leakage flow through mid-passage gap. International Journal of Turbomachinery, 2021, 167: 120800.
[31] Tao Z., Guo Z., Yu B., et al., Aero-thermal optimization of a gas turbine blade endwall with non-axisymmetric contouring and purge flow. International Journal of Heat and Mass Transfer, 2021, 178: 121626.
[32] Li S.-J., Lee J., Han J.-C., et al., Influence of mainstream turbulence on turbine blade platform cooling from simulated swirl purge flow. Applied Thermal Engineering, 2016, 101: 678–685.
[33] Zhang K., Li J., Li Z., et al., Effects of simulated swirl purge flow and mid-passage gap leakage on turbine blade platform cooling and suction surface phantom cooling performance. International Journal of Heat and Mass Transfer, 2019, 129: 618–634.
[34] Yao Y., Tao Z., Wang J., et al., The effects of swirling purge leakage on aerothermal performance of flat and non-axisymmetric endwalls. International Communications in Heat and Mass Transfer, 2023, 142: 106669.
[35] Tao Z., Li F., Yu B., et al., Effects of the positive pre-swirl purge flow on endwall aero-thermal performance of a gas turbine blade. International Journal of Thermal Sciences, 2021, 163: 106805.
[36] Zhang K., Li Z., Li J., et al., Non-axisymmetric endwall contour optimization and performance assessment as affected by simulated swirl purge flow and backward hole injection. International Journal of Thermal Sciences, 2022, 172: 107297.
[37] Du K., Chen Q., Li Y., Sunden B., Liu C., Li W., Numerical investigation on flow and cooling characteristics of a micro-ribbed vane endwall. Journal of Thermal Science, 2023, 32(2): 786–799.
[38] Zhou W., Shao H., Qenawy M., Peng D., Hu H., Liu Y., Improved turbine vane endwall film cooling by using sand-dune-inspired design. Journal of Thermal Science, 2022, 31(3): 958–973.
[39] Gai Z., Zhu P., Hu J., Liu Z., Yin H., Effects of sealing flow supply configuration with holes on sealing effectiveness of turbine rim seal. Journal of Thermal Science, 2022, 32(1): 366–386.
[40] Suryanarayanan A., Mhetras S.P., Schobeiri M.T., et al., Film-cooling effectiveness on a rotating blade platform. Journal of Turbomachinery-Transactions of the ASME, 2009, 131(1): 011014.
[41] Chen Z., Su X., Yuan X., Cooling performance of the endwall vertical hole considering the interaction between cooling jet and leading-edge horseshoe vortex. Journal of Thermal Science, 2022, 31(5): 1696–1708.
[42] Xiao X., Wang P., Du Q., Xu Q., Liu J., Zhu J., Numerical investigations of film cooling characteristics of interrupted slot and trench holes on a vane endwall. Journal of Thermal Science, 2021, 30(3): 1010–1024.
[43] Du K., Li Z., Li J., Effects of trenched film hole configurations on the endwall film cooling and suction side phantom cooling. Journal of Thermal Science, 2019, 28(5): 905–914.
Outlines

/