On Organization of Thermal Shield in a Section of a Turbine Guide Vane Leading Edge with Pulsed Blowing
The study focuses on augmentation of film cooling effectiveness in a section of a guide vane leading edge in the case of pulsed blowing through cylindrical holes. Various combinations of the blowing ratio and angle of attack at characteristic points of the leading edge contour were analyzed. Experimental research confirmed feasibility of pulsed blowing only for certain angles of attack.
Authors
- A. V. Il’inkov
- V. B. Yavkin
- A. V. Starodumov
- A. V. Shchukin
- V. V. Takmovtsev
Institutions
- Kazan State Technical University named after A. N. Tupolev (RU)
- Myasishchev Design Bureau (Russia) (RU)
Publication Details
- Journal
- Russian Aeronautics
- Published
- 2025-09-01
- DOI
- https://doi.org/10.3103/s1068799825030201
- Primary Topic
- Turbomachinery Performance and Optimization
- Type
- article
- Field-Weighted Citation Impact
- 0.00