Volume 19, Issue 5 (May 2019)                   Modares Mechanical Engineering 2019, 19(5): 1209-1220 | Back to browse issues page

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Babaei A, Aghaei Togh R, Nobakhti M, Montazeri M. Numerical Investigation of the Effects of Minor Geometric Changes of the Stator Blade Profiles on the Steady Performance of a High-pressure Gas-turbine. Modares Mechanical Engineering 2019; 19 (5) :1209-1220
URL: http://mme.modares.ac.ir/article-15-24255-en.html
1- Mechanical Engineering Department, Mechanics, Electrical Power & Computer Faculty, Science & Research Branch, Islamic Azad University, Tehran, Iran
2- Aerospace Engineering Department, Engineering Faculty, Science & Research Branch, Islamic Azad University, Tehran, Iran , reza_tog@srbiau.ac.ir
3- Aerospace Engineering Faculty, K. N. Toosi University of Technology, Tehran, Iran
Abstract:   (3356 Views)
In the high-pressure gas-turbines, with hot-flowing gas through the stator channels with a high mass-flow rate, even slight variation in the blade geometry will have significant effects on the downstream flow-field. These minor changes can be compared to corrosion rates. The first occurrence of this corrosion is the non-uniformity of flow in the stator-rotor axial distance. This non-uniform flow, due to the complex pattern of vortices, prevents the complete transfer of fluid energy to the rotor and greatly reduces the turbine performance. In this research, a high-pressure turbine is considered to be at high risk of corrosion. The main goal is to predict these variations due to corrosion. Firstly, a 3D numerical analysis of the turbine initial model was conducted to accurately observe the flow field and the results were validated by the existing experimental results. Then, in order to investigate the effects of corrosion on the turbin performance, the blades geometrical changes were applied in stator blade profile and the flow distribution was analyzed. Results show that the highest corrosion risk is at the trailing-edge of the blades. Due to reduction in the stator inlet-outlet area ratio, the axial-velocity is reduced. But simultaneously, with increasing the stator channels outlet area, the mass-flow rate is increased by 7.31%. Therefore, the turbine undergoes to an off-design condition. The flow pattern will be more complicated in the rotor's entrance, and corrosion will develop rapidly due to temperature rise as the flow separates from the rotor blades.
Full-Text [PDF 1416 kb]   (2873 Downloads)    
Article Type: Original Research | Subject: Computational Fluid Dynamic (CFD)
Received: 2018/08/19 | Accepted: 2018/12/14 | Published: 2019/05/1

References
1. Aghaei Tog R, Mesgarpoor Tousi A. Experimental evaluation of supersonic turbine characteristic curve at full and partial admission in turbine test rig. Journal of Applied and Computational Sciences in Mechanics. 2017;28(2):1-20. [Persian] [Link]
2. Aghaei Tog R, Mesgarpoor Tousi A, Tourani A. Comparison of turbulence methods in CFD analysis of compressible flows in radial turbomachines. Aircraft Engineering and Aerospace Technology. 2008;80(6):657-665. [Persian] [Link]
3. Eliaz N, Shemesh G, Latanision RM. Hot corrosion in gas turbine components. Engineering Failure Analysis. 2002;9(1):31-43. [Link] [DOI:10.1016/S1350-6307(00)00035-2]
4. Huda Z. Metallurgical failure analysis for a blade failed in a gas-turbine engine of a power plant. Materials and Design. 2009;30(8):3121-3125. [Link] [DOI:10.1016/j.matdes.2008.11.030]
5. Chahartaghi M, Ghatee M, Samaeenia A, Karrabi H. Study and numerical simulation of blades corrosion effects on a commercial axial turbine performance. Modares Mechanical Engineering. 2015;14(15):279-289. [Persian] [Link]
6. Wang Z, Ma J, Wang S, Wang M. Investigation on the effects of blade corrosion on compressor performance. Journal of the Chinese Institute of Engineers. 2016;39(7):816-824. [] [DOI:10.1080/02533839.2016.1208541]
7. Montis M, Niehuis R, Guidi M, Salvadori S, Martelli F, Stephan B. Experimental and numerical investigation on the influence of trailing edge bleeding on the aerodynamics of a NGV cascade. ASME Turbo Expo 2009: Power for Land, Sea, and Air, 8-12 June, 2009, Orlando, Florida, USA. New York: American Society of Mechanical Engineers; 2009. 10- Bannazadeh R, Riahi M, Aieneravaie M. Failure analysis of a gas turbine blade made of inconel 738LC super alloy. Amirkabir Journal of Mechanical Engineering. 2018;50(1):103-112. [Persian] 11- Aligoodarz MR, Derakhshan F, Karrabi H. Numerical analysis of blade roughness effects on gas turbine performance and flow field. Modares Mechanical Engineering. 2014;13(13):112-120. [Persian] 14- Chahartaghi M, Ghatee M, Samaeenia A, Karrabi H. Numerical simulation of roughness effects on two stage turbine performance with full cooling. Modares Mechanical Engineering. 2014;13(13):143-156. [Persian] 15- Saberi R, Fathali M. Investigation of different turbulence models performance on high-turning turbine blade loading calculations. Amirkabir Journal of Science and Research. 2015;47(1):1-12. [Persian] 16- ANSYS. Ansys Help Document, user's Guide, Mesh data, Version 16.1 [Internet]. Canonsburg: ANSYS, Inc; 2016 [cited 2018 Aug 01]. Available from: Not Found [Link]
8. Gao K, Xie Y, Zhang D. Effects of stator blade camber and surface viscosity on unsteady flow in axial turbine. Applied Thermal Engineering. 2017;118:748-764. [Link] [DOI:10.1016/j.applthermaleng.2017.03.024]
9. Hamed A, Tabakoff WC, Wenglarz RV. Erosion and deposition in turbomachinery. Journal of Propulsion and Power. 2006;22(2):350-360. [Link] [DOI:10.2514/1.18462]
10. Bannazadeh R, Riahi M, Aieneravaie M. Failure analysis of a gas turbine blade made of inconel 738LC super alloy. Amirkabir Journal of Mechanical Engineering. 2018;50(1):103-112. [Persian] [Link]
11. Aligoodarz MR, Derakhshan F, Karrabi H. Numerical analysis of blade roughness effects on gas turbine performance and flow field. Modares Mechanical Engineering. 2014;13(13):112-120. [Persian] 14- Chahartaghi M, Ghatee M, Samaeenia A, Karrabi H. Numerical simulation of roughness effects on two stage turbine performance with full cooling. Modares Mechanical Engineering. 2014;13(13):143-156. [Persian] 15- Saberi R, Fathali M. Investigation of different turbulence models performance on high-turning turbine blade loading calculations. Amirkabir Journal of Science and Research. 2015;47(1):1-12. [Persian] 16- ANSYS. Ansys Help Document, user's Guide, Mesh data, Version 16.1 [Internet]. Canonsburg: ANSYS, Inc; 2016 [cited 2018 Aug 01]. Available from: Not Found [Link]
12. Bai T, Liu J, Zhang W, Zou Z. Effect of surface roughness on the aerodynamic performance of turbine blade cascade. Propulsion and Power Research. 2014;3(2):82-89. [Link] [DOI:10.1016/j.jppr.2014.05.001]
13. Gaetani P, Persico G, Osnaghi C. Effects of axial gap on the vane-rotor interaction in a low aspect ratio turbine stage. Journal of Propulsion and Power. 2010;26(2):325-334. [Link] [DOI:10.2514/1.37616]
14. 14- Chahartaghi M, Ghatee M, Samaeenia A, Karrabi H. Numerical simulation of roughness effects on two stage turbine performance with full cooling. Modares Mechanical Engineering. 2014;13(13):143-156. [Persian] [Link]
15. Saberi R, Fathali M. Investigation of different turbulence models performance on high-turning turbine blade loading calculations. Amirkabir Journal of Science and Research. 2015;47(1):1-12. [Persian] [Link]
16. ANSYS. Ansys Help Document, user's Guide, Mesh data, Version 16.1 [Internet]. Canonsburg: ANSYS, Inc; 2016 [cited 2018 Aug 01]. Available from: Not Found [Link]
17. Aghaei Togh R, Mesgarpoor Tousi A. Effects of nozzle arrangement angle on the performance of partially admitted turbines. Journal of Mechanical Science and Technology. 2018;32(1):455-464. [Link] [DOI:10.1007/s12206-017-1247-1]

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