Theoretical and Natural Science
- The Open Access Proceedings Series for Conferences
Theoretical and Natural Science
Vol. 18, 08 December 2023
Open
Access | Article
Optimization of the two-dimensional stator
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Abstract
Gas turbine engine is mainly composed of compressor, inlet , tail nozzle, combustion chamber and turbine. The compressor pressurizes the air from the inlet into high-pressure air, which is used to mix and burn with fuel in the combustion chamber to form high-pressure gas. In this paper, numerical analysis of compressor stator performance and corresponding optimization were conducted using COMSOL Multiphysics 5.6. Firstly, an overview of compressor blade design is given. Then, the physical model and computational model are introduced and established by COMSOL. Afterwards, after the validation of the computational model, the numerical computations and results are generated and used to compare with NASA67 stator experimental data, with several key performance indicators including turning angle and loss coefficient. The polynomial expression is used to construct the blade shape/profile with different maximum thickness and its position, maximum bending and its position, trailing and leading edge angle and chord length are chosen as parameters for optimization. Then, I choose the maximum thickness and its position, maximum bending and its position, trailing and leading edge angle as the optimization parameter. Finally, we reach some conclusions of a better stator design possible for newer compressor requirements and further studies are recommended.
Keywords
optimization, stator, compressor
References
1. Schlichting, H., and Truckenbrodt, E. (1979) Aerodynamics of the Airplane (Translated by H. J. Ramm). McGraw-Hill International Book Company.
2. Kulfan, B. M., and Bussoletti, J. E. (2006). Fundamental parametric geometry representations for aircraft component shapes. AIAA Paper 2006-6948, 1-45.
3. Schreiber, H. A., Steinert, W., Sonoda, T., and Arima, T. (2004). Advanced high-turning compressor airfoils for low Reynolds number condition - part II: Experimental and numerical analysis. J. Turbomachinery, 126 (4), 482-492. doi:10.1115/1.1737780
4. Giesecke, D., Stark, U., Harms García, R., and Friedrichs, J. (2017). Design and Optimization of Compressor Airfoils by Using Class Function / Shape Function
5. Methodology. 17th International Symposium on Transport Phenomena and Dynamics of Rotating Machinery (ISROMAC).
6. Daniel Giesecke, Marcel Bullert, Jens Friedrichs TU Braunschweig (2018). Optimization of high subsonic, high Reynolds number axial compressor airflow sections for increasing operating range. GPPS-2018-47
Data Availability
The datasets used and/or analyzed during the current study will be available from the authors upon reasonable request.
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- Volume Title
- Proceedings of the 2nd International Conference on Computing Innovation and Applied Physics
- ISBN (Print)
- 978-1-83558-201-5
- ISBN (Online)
- 978-1-83558-202-2
- Published Date
- 08 December 2023
- Series
- Theoretical and Natural Science
- ISSN (Print)
- 2753-8818
- ISSN (Online)
- 2753-8826
- DOI
- 10.54254/2753-8818/18/20230365
- Copyright
- 08 December 2023
- Open Access
- This article is an open access article distributed under the terms and conditions of the Creative Commons Attribution (CC BY) license, which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited