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Author:

Wu, Chenqi (Wu, Chenqi.) | He, Kun (He, Kun.) | Yan, Xin (Yan, Xin.)

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Abstract:

Numerical methods were adopted to study the film cooling and heat transfer performance on the pressure-side (P. S.) winglet-squealer tip of a turbine stage under engine condition. The heat transfer coefficient and film cooling effectiveness on the winglet-squealer tip were computed at five different streamwise ejection angles, three different numbers of cooling hole with P. S. defection, and four different P. S. defection angles. The improvement of the film cooling effect and mitigation of heat transfer on the winglet-squealer tip were achieved based on the present study. The results show that the inclined coolant ejection is effective to improve the film cooling effect and reduce the heat transfer on the P. S. winglet-squealer tip of a turbine stage. As the streamwise ejection angle increases, the heat transfer coefficient on tip decreased at first and then increased. If the streamwise ejection angle equals to 120 degree, the area-averaged heat transfer coefficient on the tip surface decreased by 28. 26 %, and the area-averaged film cooling effectiveness increased by 33. 86% as compared with the vertical ejection case. Adjusting the ejection angles for five tip cooling holes near leading edge towards the P. S. is beneficial for film cooling effect improvement on the cavity floor near the front part. Compared to the case that all tip holes deflection towards the S. S., the area-averaged heat transfer coefficient on the tip surface decreased by 15.65%, and the area-averaged film cooling effectiveness increased by 9. 51 %. As the ejection angles for five middle-camber holes near leading edge towards the P. S. equal to 60 degree, the best film cooling and heat transfer performance on the winglet-squealer tip are achieved. In this case, the area-averaged heat transfer coefficient on tip surface decreased by 38. 84 %, and the area-averaged film cooling effectiveness increased by 42. 24%, as compared with the vertical ejection case. Moreover, the uniformity of film coolant coverage on the winglet-squealer tip is improved significantly. © 2022 Xi'an Jiaotong University. All rights reserved.

Keyword:

Coolants Film cooling Gas turbines Heat transfer coefficients Numerical methods

Author Community:

  • [ 1 ] [Wu, Chenqi]School of Energy and Power Engineering, Xi'an Jiaotong University, Xi'an; 710049, China
  • [ 2 ] [He, Kun]School of Energy and Power Engineering, Xi'an Jiaotong University, Xi'an; 710049, China
  • [ 3 ] [Yan, Xin]School of Energy and Power Engineering, Xi'an Jiaotong University, Xi'an; 710049, China

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Source :

Journal of Xi'an Jiaotong University

ISSN: 0253-987X

Year: 2022

Issue: 7

Volume: 56

Page: 27-37

Cited Count:

WoS CC Cited Count:

SCOPUS Cited Count: 2

ESI Highly Cited Papers on the List: 0 Unfold All

WanFang Cited Count:

Chinese Cited Count:

30 Days PV: 6

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