Study on rotational effects of modern turbine blade on coolant injecting nozzle position with film cooling and vortex composite performance

• المؤلفون الرئيسيون: Wang, Jiefeng, Ng, Eddie Yin Kwee, Li, Jianwu, Cao, Yanhao, Huang, Yanan, Li, Liang
• مؤلفون آخرون: School of Mechanical and Aerospace Engineering
• التنسيق: مقال
• اللغة: English
• منشور في: 2024
• الموضوعات: Engineering::Mechanical engineering; Vortex Cooling; Injecting Nozzle Location
• الوصول للمادة أونلاين: https://hdl.handle.net/10356/173182
• المؤسسة: Nanyang Technological University

The flow structure of the vortex cooling is asymmetrical compared to the traditional gas turbine leading edge cooling, such as the impingement cooling and the axial f low cooling. This asymmetrical property will affect the cooling performance in the blade leading edge, whereas such effects are not f...