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Influence of the upstream slot geometry on the endwall cooling and phantom cooling of vane suction side surface

Du, Kun LU ; Li, Zhigang; Li, Jun and Sunden, Bengt LU (2017) In Applied Thermal Engineering 121. p.688-700
Abstract

Modern gas turbines always operate at a high level of inlet temperature. The current inlet temperature in the aircraft and heavy duty gas turbines is higher than the melting point of the guide vane material. Consequently, advanced cooling schemes must be developed to ensure the safe operation of gas turbines. In the current study, numerical simulations were conducted to investigate the influence of the upstream slot geometry on the endwall cooling and phantom cooling of the vane suction side surface. Three-dimensional (3D) Reynolds-averaged Navier–Stokes (RANS) equations combined with the shear stress transport (SST) k-ω turbulence model were solved to conduct the simulations based on the validated turbulence model. The results indicate... (More)

Modern gas turbines always operate at a high level of inlet temperature. The current inlet temperature in the aircraft and heavy duty gas turbines is higher than the melting point of the guide vane material. Consequently, advanced cooling schemes must be developed to ensure the safe operation of gas turbines. In the current study, numerical simulations were conducted to investigate the influence of the upstream slot geometry on the endwall cooling and phantom cooling of the vane suction side surface. Three-dimensional (3D) Reynolds-averaged Navier–Stokes (RANS) equations combined with the shear stress transport (SST) k-ω turbulence model were solved to conduct the simulations based on the validated turbulence model. The results indicate that the adiabatic cooling effectiveness in the upstream region of the stagnation is significantly increased by introducing the contoured upstream slot. However, the normal upstream slot obtains a relatively high adiabatic cooling effectiveness level in the downstream region of the stagnation. In the present research, the case with normalized amplitude A‾=0.75, initial phase angle φ=45° achieves the largest overall adiabatic cooling effectiveness near the vane leading edge. In contrast, the case with A‾=0.75, φ=30° attains the smallest overall adiabatic cooling effectiveness on the endwall surface. Moreover, the phantom cooling effectiveness on the vane suction side surface is relatively small relative to the adiabatic cooling effectiveness on the endwall. The case with the normal upstream slot achieves the largest phantom cooling effectiveness on the vane suction side surface compared with the contoured upstream slot. Overall, the contoured upstream slot significantly enhances the endwall cooling effectiveness by rearranging the distribution of the coolant mass flowrate at the slot outlet.

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Please use this url to cite or link to this publication:
author
organization
publishing date
type
Contribution to journal
publication status
published
subject
keywords
Numerical simulations, Phantom cooling, Upstream slot geometry, Vane endwall
in
Applied Thermal Engineering
volume
121
pages
13 pages
publisher
Elsevier
external identifiers
  • scopus:85018754446
  • wos:000406169600064
ISSN
1359-4311
DOI
10.1016/j.applthermaleng.2017.04.143
language
English
LU publication?
yes
id
c39f156d-d944-49e4-8cd2-f54c03583ccb
date added to LUP
2017-05-23 13:47:09
date last changed
2017-09-18 11:36:59
@article{c39f156d-d944-49e4-8cd2-f54c03583ccb,
  abstract     = {<p>Modern gas turbines always operate at a high level of inlet temperature. The current inlet temperature in the aircraft and heavy duty gas turbines is higher than the melting point of the guide vane material. Consequently, advanced cooling schemes must be developed to ensure the safe operation of gas turbines. In the current study, numerical simulations were conducted to investigate the influence of the upstream slot geometry on the endwall cooling and phantom cooling of the vane suction side surface. Three-dimensional (3D) Reynolds-averaged Navier–Stokes (RANS) equations combined with the shear stress transport (SST) k-ω turbulence model were solved to conduct the simulations based on the validated turbulence model. The results indicate that the adiabatic cooling effectiveness in the upstream region of the stagnation is significantly increased by introducing the contoured upstream slot. However, the normal upstream slot obtains a relatively high adiabatic cooling effectiveness level in the downstream region of the stagnation. In the present research, the case with normalized amplitude A‾=0.75, initial phase angle φ=45° achieves the largest overall adiabatic cooling effectiveness near the vane leading edge. In contrast, the case with A‾=0.75, φ=30° attains the smallest overall adiabatic cooling effectiveness on the endwall surface. Moreover, the phantom cooling effectiveness on the vane suction side surface is relatively small relative to the adiabatic cooling effectiveness on the endwall. The case with the normal upstream slot achieves the largest phantom cooling effectiveness on the vane suction side surface compared with the contoured upstream slot. Overall, the contoured upstream slot significantly enhances the endwall cooling effectiveness by rearranging the distribution of the coolant mass flowrate at the slot outlet.</p>},
  author       = {Du, Kun and Li, Zhigang and Li, Jun and Sunden, Bengt},
  issn         = {1359-4311},
  keyword      = {Numerical simulations,Phantom cooling,Upstream slot geometry,Vane endwall},
  language     = {eng},
  month        = {07},
  pages        = {688--700},
  publisher    = {Elsevier},
  series       = {Applied Thermal Engineering},
  title        = {Influence of the upstream slot geometry on the endwall cooling and phantom cooling of vane suction side surface},
  url          = {http://dx.doi.org/10.1016/j.applthermaleng.2017.04.143},
  volume       = {121},
  year         = {2017},
}