Flow field modeling and performance improving of an axial turbine's using Adjoint method

Authors

1 Aerodynamics & Propulsion, Aerospace Engineering, Malek Ashtar University O Tech., Tehran, Iran

2 Aerodynamics & Propulsion, Aerospace Engineering, Malek Ashtar University Of Tech. , Tehran, Iran

3 Mechanical & Aerospace Engineering, Engineering Faculty, ., Science & Research branch of Islamic Azad Univ., Tehran, Iran

4 Aerodynamics & propulsion, Aero. Eng., Sharif Univ. of Tech., Tehran, Iran

Abstract

In recent years, optimization of Turbomachinery performance parameters is one of the most important topics for researchers and industrial scholars. The aerodynamic optimization of blades has been done by variety of algorithms and methods until now; however new tools have better suggestions in this field.
This paper reports a 3D numerical analysis and geometrical optimization of fully turbulent flow around a turbine's rotor blades. Numerical analysis is done using the AUSM+ scheme and SST k –ω turbulence model. An Ad-joint Algorithm gradient method is used in geometrical aerodynamic optimization of blades. This algorithm has been used previously for 2D models as build-in codes and for 3D models is done for the first time in this research.
The total to total isentropic efficiency as objective function and other performance parameters have a good agreement with the experimental measurements in validation process. Through the optimization process, the objective function is improved by 0.18, which in comparison with others' reported works is a good progress in performance improvement.

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References

[1] Kammerer S, Mayer J, Stetter H, Paffrath M, Wever U, Jung A (2004) Development of a three-dimensional geometry optimization method for turbomachinery applications. Int J Rotat Machin 10(5): 373-385.
[2] Cho SY, Choi HJ, Kim C (2011) Design of cascade model using an optimization method. IEEE, Asia-Pacific University of Tech. & Innovation, Kuala Lumpur, Malaysia.
[3] Chen L, Chen J (2015) Aerodynamic optimization design of multi-stage turbine using the continuous Adjoint method. Int J Turbo Jet-Engin 32(2): 24.
[4] Montanelli H, Montagnac M, Gallard F (2015)   Gradient span analysis method: application to the multipoint aerodynamic shape optimization of a turbine cascade. J Turbomach 137(9):  091006.
[5] جوادی س م، وحیدی­فر س، مه­پیکر م ر، تیمورتاش ع ر (1385) بهینه­سازی منحنی پره­های توربین با هدف کاهش تلفات و افزایش سرعت خروجی با استفاده از الگوریتم ژنتیک. چهاردهمین کنفرانس سالانه مهندسی مکانیک، اصفهان، دانشگاه صنعتی اصفهان 8-1.
[6] صادقی س، حمیدی ح ا (1392) بهینه سازی شکل ایرفویل کسکید توربوماشین­ها به وسیله الگوریتم ژنتیک. هفتمین کنفرانس دانشجویی مهندسی مکانیک، تهران، دانشگاه صنعتی امیرکبیر 6-1.
[7] ANSYS® Ansys Fluent, Release 15.0, Help    System, Fluent theory guide, ANSYS, Inc.
[8] Tog R, Tousi A (2013) Experimental and numerical investigation of design optimization of a partial admitted supersonic turbine. Propul Power 2: 70-83.
[9] Dixon SL, Hall CA (2014) Fluid mechanics and thermodynamics of turbomachinery. 7th edn. Elsevier, Amsterdam.
Journal of Solid and Fluid Mechanics
Volume 8, Issue 1
April 2018
Pages 127-133

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