Optimization of Gas Turbine Blade Cooling System
Kanagaraja.K1, Jegadeeswari.G2, Kirubadurai.B3
1Kanagaraja.K, Department of Mechanical Engineering, Rajalakshmi Institute of Technology, Chennai, India.
2Jegadeeswari .G, Department of Electrical and Electronics Engineering, AMET Deemed to be University, Chennai, India.
3Kirubadurai.B, Department of Aeronautical Engineering, Vel Tech Dr. Rangarajan Dr. Sagunthala R&D Institute of Science & Technology, Chennai, India.
Manuscript received on 21 August 2019. | Revised Manuscript received on 06 September 2019. | Manuscript published on 30 September 2019. | PP: 4176-4181 | Volume-8 Issue-11, September 2019. | Retrieval Number: K21630981119/2019©BEIESP | DOI: 10.35940/ijitee.K2163.0981119
Open Access | Ethics and Policies | Cite | Mendeley | Indexing and Abstracting
© The Authors. Blue Eyes Intelligence Engineering and Sciences Publication (BEIESP). This is an open access article under the CC-BY-NC-ND license (http://creativecommons.org/licenses/by-nc-nd/4.0/)
Abstract: At present, Gas turbines play an essential responsibility in different areas such as jet, generating power and various commercial and industrial sectors. Melting point of the turbine blade may causes the hotness levels which go rapidly raise. Likewise, heavy crack may cause because of Turbine Inlet Temperature (TIT) at turbine blades for the period of expansion procedure of turbine sector. Hence, a highly developed blade cooling system is required for safe operation of turbines. The proposed system deals with the serpentine rip – roughened passage with micro pin fin cooling system and it has been analyzed corresponding to serpentine cooling system. It increases the heat transfer enhancement. Therefore, very warm gases in and around the turbine blade may have a stream temperature at 1500K. On the other side, cool air disclosed to the blade core duct and an entry temperature may have been 650K. The proposed systems with 2D and 3D model were developed by using CATIA. The 3D design is then analyzed using CFD. Further, the corresponding results of serpentine rip – roughened passage and micro pin fin arrangement in serpentine rip-roughened passage are compared and the details are presented.
Keywords: Gas Turbines, Turbine Inlet Temperature (TIT), CFD, Cooling system, CATIA
Scope of the Article: Discrete Optimization