Advanced

Design of Full-Scale Endwall Film Cooling of a Turbine Vane

Liu, Jian LU ; Du, Wei LU ; Zhang, Guohua LU ; Hussain, Safeer LU ; Wang, Lei LU ; Xie, Gongnan LU and Sundén, Bengt LU (2020) In Journal of Heat Transfer 142(2).
Abstract

Endwall film cooling is a significant cooling method to protect the endwall region and the junction region of endwall and a turbine vane, where usually a relatively high temperature load exists. This work aims to find the optimized arrangement of film cooling holes on the endwall and improve the film cooling in some difficult regions on the endwall, such as pressure side-endwall junction region. Several ideas for film cooling hole arrangement design are proposed, based on the pressure coefficient distribution, the streamline distribution, and the heat transfer coefficient (HTC) distribution, respectively. Four specified designs are built and compared. The results are obtained by numerical calculations with a well-validated turbulence... (More)

Endwall film cooling is a significant cooling method to protect the endwall region and the junction region of endwall and a turbine vane, where usually a relatively high temperature load exists. This work aims to find the optimized arrangement of film cooling holes on the endwall and improve the film cooling in some difficult regions on the endwall, such as pressure side-endwall junction region. Several ideas for film cooling hole arrangement design are proposed, based on the pressure coefficient distribution, the streamline distribution, and the heat transfer coefficient (HTC) distribution, respectively. Four specified designs are built and compared. The results are obtained by numerical calculations with a well-validated turbulence model, the k-ω shear stress transport (SST) model. From this work, the designs based on the pressure coefficient distribution (designs 1 and 2) force the flow from the pressure side to the suction side (SS), especially in design 2, which adopts compound angle holes. The designs based on pressure coefficients have benefit in the cooling of the SS but give worse coolant coverage on the pressure side. In addition, designs 1 and 2 have little influence on the original pressure field. The design based on the streamline distributions (design 3) has larger coolant coverage on the endwall and provides good coolant coverage on the endwall and pressure side junction region. The design based on the HTC distribution provides large overall film cooling effectiveness on both the pressure side and the SS. More film cooling holes are placed on the high temperature regions, which is more effective in practice.

(Less)
Please use this url to cite or link to this publication:
author
; ; ; ; ; and
organization
publishing date
type
Contribution to journal
publication status
published
subject
keywords
compound angle holes, film cooling, optimized arrangement, turbine vane
in
Journal of Heat Transfer
volume
142
issue
2
article number
022201
publisher
American Society Of Mechanical Engineers (ASME)
external identifiers
  • scopus:85092142128
ISSN
0022-1481
DOI
10.1115/1.4045069
language
English
LU publication?
yes
id
6b49f23f-b20a-4c9a-9da9-a21fac4cb494
date added to LUP
2020-11-06 14:58:32
date last changed
2020-11-07 01:41:32
@article{6b49f23f-b20a-4c9a-9da9-a21fac4cb494,
  abstract     = {<p>Endwall film cooling is a significant cooling method to protect the endwall region and the junction region of endwall and a turbine vane, where usually a relatively high temperature load exists. This work aims to find the optimized arrangement of film cooling holes on the endwall and improve the film cooling in some difficult regions on the endwall, such as pressure side-endwall junction region. Several ideas for film cooling hole arrangement design are proposed, based on the pressure coefficient distribution, the streamline distribution, and the heat transfer coefficient (HTC) distribution, respectively. Four specified designs are built and compared. The results are obtained by numerical calculations with a well-validated turbulence model, the k-ω shear stress transport (SST) model. From this work, the designs based on the pressure coefficient distribution (designs 1 and 2) force the flow from the pressure side to the suction side (SS), especially in design 2, which adopts compound angle holes. The designs based on pressure coefficients have benefit in the cooling of the SS but give worse coolant coverage on the pressure side. In addition, designs 1 and 2 have little influence on the original pressure field. The design based on the streamline distributions (design 3) has larger coolant coverage on the endwall and provides good coolant coverage on the endwall and pressure side junction region. The design based on the HTC distribution provides large overall film cooling effectiveness on both the pressure side and the SS. More film cooling holes are placed on the high temperature regions, which is more effective in practice. </p>},
  author       = {Liu, Jian and Du, Wei and Zhang, Guohua and Hussain, Safeer and Wang, Lei and Xie, Gongnan and Sundén, Bengt},
  issn         = {0022-1481},
  language     = {eng},
  number       = {2},
  publisher    = {American Society Of Mechanical Engineers (ASME)},
  series       = {Journal of Heat Transfer},
  title        = {Design of Full-Scale Endwall Film Cooling of a Turbine Vane},
  url          = {http://dx.doi.org/10.1115/1.4045069},
  doi          = {10.1115/1.4045069},
  volume       = {142},
  year         = {2020},
}