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Napat Kanjeakphong. Numerical study on performance of crossover jet impingement cooling at trailing edge of gas turbine blade with and without rotation. Master's Degree(Mechanical Engineering Simulation and Design (International Program)). King Mongkut's University of Technology North Bangkok. Central Library. : King Mongkut's University of Technology North Bangkok, 2022.
Numerical study on performance of crossover jet impingement cooling at trailing edge of gas turbine blade with and without rotation
Name: Napat Kanjeakphong
LCSH:
Numerical analysis
LCSH:
Heat
-- Transmission
LCSH:
Gas-turbines
Abstract:
The performance of gas turbine engines can be improved by increasing the turbine inlet temperature beyond the melting point of material. Therefore, the trailing edge of a gas turbine blade requires the effective internal cooling methods because the narrow shape of the trailing-edge region constrains the internal cooling passage. The impingement of a rib-roughened cooling technique is utilized to reduce the turbine blade temperature to prevent the turbine blade thermal failures. This paper presents the numerical study of the 3D steady flow and the cooling effectiveness indicated by the Nusselt number distribution at the 11 target surfaces based on the Reynolds-Averaged Navier-Stokes (RANS) equations coupled with the energy equation using 5 turbulence models: Spalart-Allmaras, Wilcox k-ω, SST k-ω, realizable k-ɛ with enhanced wall treatment and RNG k-ɛ with enhanced wall treatment. The purpose of this study is to investigate the effect of rotation on the crossover jet impingement cooling method for gas turbine blade cooling. To simulate realistic operating conditions, the cooling passage is rotated, and the cooling effectiveness and flow behavior are evaluated using computational fluid dynamics (CFD). For this investigation, the Spalart-Allmaras turbulence model is shown to be the most accurate. The area-weighted average Nusselt number is computed for both the stationary and rotational cases, and the results show that the rotational case outperforms the stationary case in terms of overall cooling effectiveness. Temperature contour plots reveal the possibility of thermal failure at the 1st target surface due to high temperature. The coolant deviation is observed in both cases, with the coolant impingement beneath the rib in the rotational case. This study emphasizes the importance of coolant deviation and the need for further research to optimize coolant flow and reduce the risk of thermal failure.
King Mongkut's University of Technology North Bangkok. Central Library
Address:
BANGKOK
Email:
library@kmutnb.ac.th
Name: Ekachai Juntasaro
Role:
thesis advisor
Email :
ekachai.j.mesd@tggs-bangkok.org
Created:
2022
Modified:
2567-08-19
Issued:
2024-08-19
วิทยานิพนธ์/Thesis
application/pdf
eng
DegreeName: Master of Engineering
Level: Master's Degree
©copyrights King Mongkut's University of Technology North Bangkok
RightsAccess:
ใช้เวลา
0.027491 วินาที
Napat Kanjeakphong
| Title | Contributor | Type |
|---|---|---|
| Numerical study on performance of crossover jet impingement cooling at trailing edge of gas turbine blade with and without rotation
มหาวิทยาลัยเทคโนโลยีพระจอมเกล้าพระนครเหนือ Napat Kanjeakphong | Ekachai Juntasaro | วิทยานิพนธ์/Thesis |
| Numerical study on performance of crossover jet impingement cooling at trailing edge of gas turbine blade with and without rotation
มหาวิทยาลัยเทคโนโลยีพระจอมเกล้าพระนครเหนือ Napat Kanjeakphong;Phongsakorn Thawornsathit;Varangrat Juntasaro;Pipat Tansakul;Panut Bumphenkiattikul;Arthit Vongachariya;Ekachai Juntasaro | บทความ/Article |
Ekachai Juntasaro