Version 1
: Received: 28 July 2023 / Approved: 28 July 2023 / Online: 28 July 2023 (09:54:15 CEST)
How to cite:
Wang, J.; NG, E.Y.K.; Li, J.; Huang, Y.; Cao, Y.; Li, L. Study on Effects of Modern Turbine Blade Coolant Injecting Nozzle Position on Film Cooling and Vortex Composite Performance under Rotating Conditions. Preprints2023, 2023071983. https://doi.org/10.20944/preprints202307.1983.v1
Wang, J.; NG, E.Y.K.; Li, J.; Huang, Y.; Cao, Y.; Li, L. Study on Effects of Modern Turbine Blade Coolant Injecting Nozzle Position on Film Cooling and Vortex Composite Performance under Rotating Conditions. Preprints 2023, 2023071983. https://doi.org/10.20944/preprints202307.1983.v1
Wang, J.; NG, E.Y.K.; Li, J.; Huang, Y.; Cao, Y.; Li, L. Study on Effects of Modern Turbine Blade Coolant Injecting Nozzle Position on Film Cooling and Vortex Composite Performance under Rotating Conditions. Preprints2023, 2023071983. https://doi.org/10.20944/preprints202307.1983.v1
APA Style
Wang, J., NG, E.Y.K., Li, J., Huang, Y., Cao, Y., & Li, L. (2023). Study on Effects of Modern Turbine Blade Coolant Injecting Nozzle Position on Film Cooling and Vortex Composite Performance under Rotating Conditions. Preprints. https://doi.org/10.20944/preprints202307.1983.v1
Chicago/Turabian Style
Wang, J., Yanhao Cao and Liang Li. 2023 "Study on Effects of Modern Turbine Blade Coolant Injecting Nozzle Position on Film Cooling and Vortex Composite Performance under Rotating Conditions" Preprints. https://doi.org/10.20944/preprints202307.1983.v1
Abstract
This paper Numerically investigates the effectiveness of the turbine rotating blade nozzle position on the vortex and film composite cooling performance. The coolant injecting nozzles arranged near the pressure surface side (PS-side-in) .vs. arranged near the suction surface side (SS-side-in) are compared at the rotating speed range of 0-4000rpm with fluid and thermal conjugate approach. Results show that the nozzle position presents different influences under low and higher rotating speed. In terms of the mainstream flow, rotation makes the stagnation line move from the PS-side pressure surface side to the SS-side suc-tion surface side, which changes the coolant film attachment on the blade leading edge surface. The nozzle position however indicates limited influence on the coolant film flow. In terms of the internal channel vortex flow, the coolant injecting from the nozzles forms a high-velocity region near the target wall which brings about enhancing convective heat transfer. The direction of the near wall vortex flow is opposite and align to the Coriolis force direction in both the PS-side-in and SS-side-in, respectively. Therefore, the Coriolis force augments to the heat transfer of the internal vortex cooling in SS-side-in while weakens the internal heat transfer in PS-side-in. Such effects become more intense with higher rotational speed. The blade surface area-averaged dimensionless temperature that inversely proportional to the actual temperature is 7.8% higher in SS-side-in as compared to that in PS-side-in. The SS-side-in suggests more superior composite cooling perfor-mance under the relatively higher rotating speed.
Keywords
Vortex cooling; Injecting nozzle location; Gas turbine; Blade film cooling; Heat transfer
Subject
Engineering, Aerospace Engineering
Copyright:
This is an open access article distributed under the Creative Commons Attribution License which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited.
