Effects of thermal barrier coating thickness and surface roughness on cooling performance sensitivity of a turbine blade
In this study, the conjugate heat transfer method is used to research the impact of the thermal barrier coating thickness (0–300 μm) and surface roughness (Ra = 0–30 μm) on the cooling characteristics of the high-pressure turbine blade. A physical thin-walled structure is applied to simulate the TBC...
| Main Authors: | , , , |
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| Format: | Article |
| Language: | English |
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Elsevier
2023-12-01
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| Series: | Case Studies in Thermal Engineering |
| Subjects: | |
| Online Access: | http://www.sciencedirect.com/science/article/pii/S2214157X2301033X |
| _version_ | 1797422553612943360 |
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| author | Zequn Du Haiwang Li Ruquan You Yi Huang |
| author_facet | Zequn Du Haiwang Li Ruquan You Yi Huang |
| author_sort | Zequn Du |
| collection | DOAJ |
| description | In this study, the conjugate heat transfer method is used to research the impact of the thermal barrier coating thickness (0–300 μm) and surface roughness (Ra = 0–30 μm) on the cooling characteristics of the high-pressure turbine blade. A physical thin-walled structure is applied to simulate the TBC on the turbine blade surface. The results indicate that the temperature distribution on the coated metal surface is more uniform. With an increase in coating thickness, the heat flux of the blade surface decreases, reaching a maximum of 106W/m2 at the leading edge. Furthermore, leading-edge temperature is the most sensitive to changes in coating thickness, and the pressure surface is the least sensitive. The overall cooling effectiveness is less sensitive to changes in the roughness after coating. Increasing the surface roughness, the heat flux reduces at the leading edge and increases at other places. The range of the overall cooling effectiveness rate of the blade rises, and the sensitivity of the overall cooling effectiveness to the coating thickness increases. When Ra reaches 20 μm, the insulation effect with different coating thickness remains unaffected. |
| first_indexed | 2024-03-09T07:33:57Z |
| format | Article |
| id | doaj.art-1dc2133f3dfe4feca1ff5ea9f1d17dc4 |
| institution | Directory Open Access Journal |
| issn | 2214-157X |
| language | English |
| last_indexed | 2024-03-09T07:33:57Z |
| publishDate | 2023-12-01 |
| publisher | Elsevier |
| record_format | Article |
| series | Case Studies in Thermal Engineering |
| spelling | doaj.art-1dc2133f3dfe4feca1ff5ea9f1d17dc42023-12-03T05:41:28ZengElsevierCase Studies in Thermal Engineering2214-157X2023-12-0152103727Effects of thermal barrier coating thickness and surface roughness on cooling performance sensitivity of a turbine bladeZequn Du0Haiwang Li1Ruquan You2Yi Huang3Research Institute of Aero-Engine, Beihang University, Beijing, China; National Key Laboratory of Science and Technology on Aero Engines Aero-thermodynamics, Beihang University, Beijing, ChinaResearch Institute of Aero-Engine, Beihang University, Beijing, China; National Key Laboratory of Science and Technology on Aero Engines Aero-thermodynamics, Beihang University, Beijing, ChinaResearch Institute of Aero-Engine, Beihang University, Beijing, China; National Key Laboratory of Science and Technology on Aero Engines Aero-thermodynamics, Beihang University, Beijing, China; Corresponding author. Research Institute of Aero-Engine, Beihang University, Beijing, China.Research Institute of Aero-Engine, Beihang University, Beijing, China; National Key Laboratory of Science and Technology on Aero Engines Aero-thermodynamics, Beihang University, Beijing, ChinaIn this study, the conjugate heat transfer method is used to research the impact of the thermal barrier coating thickness (0–300 μm) and surface roughness (Ra = 0–30 μm) on the cooling characteristics of the high-pressure turbine blade. A physical thin-walled structure is applied to simulate the TBC on the turbine blade surface. The results indicate that the temperature distribution on the coated metal surface is more uniform. With an increase in coating thickness, the heat flux of the blade surface decreases, reaching a maximum of 106W/m2 at the leading edge. Furthermore, leading-edge temperature is the most sensitive to changes in coating thickness, and the pressure surface is the least sensitive. The overall cooling effectiveness is less sensitive to changes in the roughness after coating. Increasing the surface roughness, the heat flux reduces at the leading edge and increases at other places. The range of the overall cooling effectiveness rate of the blade rises, and the sensitivity of the overall cooling effectiveness to the coating thickness increases. When Ra reaches 20 μm, the insulation effect with different coating thickness remains unaffected.http://www.sciencedirect.com/science/article/pii/S2214157X2301033XThermal barrier coating thicknessSurface roughnessConjugate heat transferCooling performance sensitivityTurbine blades |
| spellingShingle | Zequn Du Haiwang Li Ruquan You Yi Huang Effects of thermal barrier coating thickness and surface roughness on cooling performance sensitivity of a turbine blade Case Studies in Thermal Engineering Thermal barrier coating thickness Surface roughness Conjugate heat transfer Cooling performance sensitivity Turbine blades |
| title | Effects of thermal barrier coating thickness and surface roughness on cooling performance sensitivity of a turbine blade |
| title_full | Effects of thermal barrier coating thickness and surface roughness on cooling performance sensitivity of a turbine blade |
| title_fullStr | Effects of thermal barrier coating thickness and surface roughness on cooling performance sensitivity of a turbine blade |
| title_full_unstemmed | Effects of thermal barrier coating thickness and surface roughness on cooling performance sensitivity of a turbine blade |
| title_short | Effects of thermal barrier coating thickness and surface roughness on cooling performance sensitivity of a turbine blade |
| title_sort | effects of thermal barrier coating thickness and surface roughness on cooling performance sensitivity of a turbine blade |
| topic | Thermal barrier coating thickness Surface roughness Conjugate heat transfer Cooling performance sensitivity Turbine blades |
| url | http://www.sciencedirect.com/science/article/pii/S2214157X2301033X |
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