Design of Full-Scale Endwall Film Cooling of a Turbine Vane
(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)
- author
- Liu, Jian LU ; Du, Wei LU ; Zhang, Guohua LU ; Hussain, Safeer LU ; Wang, Lei LU ; Xie, Gongnan LU and Sundén, Bengt LU
- organization
- publishing date
- 2020
- 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
- 2023-11-20 15:08:08
@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}}, keywords = {{compound angle holes; film cooling; optimized arrangement; turbine vane}}, 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}}, }