International Journal of Science and Research (IJSR) ISSN (Online): 2319-7064 Index Copernicus Value (2015): 78.96 | Impact Factor (2015): 6.391 Volume 6 Issue 6, June 2017 www.ijsr.net Licensed Under Creative Commons Attribution CC BY Appropriateness Investigations on Nimonic 901 and Rane 77 made Guide Vanes of Gas Turbine with Showerhead Cooling Dr. R. Saravanan 1 , M. Karuppasamy 2 1 Principal and Professor (Mechanical Engineering), Elenki Institute of Engineering and Technology, Hyderabad -532019, Telungana State, India 2 Associate Professor and Head of the Department of Mechanical Engineering, S.Veerasamy Chettiar College of Engg. and Tech., Puliangudi-627855, Tamil Nadu, India Abstract: Gas turbines are under the class of high temperature application thermal device. Stability of the material at elevated temperature is difficult to predict conventional methods. The design, engineering offers solution for such cases. The stability can be experimented for such cases using modeling and simulation by means of design engineering softwares. Structural stability of the material depends on the shape, material and load. It is required to analyze the structural stability of such gas turbine components at elevated temperature. The hollow portion like cooling design and greatly influences on the structural stability of them. This research focuses on the material influence on guide vane with showehead type cooling design. The high temperature materials like Nim onic 901 and Rane 77 were considered for this analysis. The Pro –E and ANSYS R14 were employed for modelling and FEM analysis respectively. Keywords: showerhead cooling, guide vane, gas turbine, Nimonic 901, Rene 77 1. Introduction Gas turbine applications are to be expected at the industries like, power generation, locomotive, aircraft, marine propulsion, and other industrial prime movers. The aim of higher output and thermal efficiency leads to higher operating temperature of thermal devices like gas turbine, In gas turbine the inlet temperature is about 1500°C [1-3]. In some special cases like aerospace, it is much higher, i.e., 1,727°C [4-6] as well as with the higher operating pressure ratio at compressor about 50 [6]. In such circumstances the components often encounter the thermal damages as well as other damages like melting, corrosion, oxidation and erosion [7], the degradation of local or global structural strengths of blades, vanes and other components and it was estimated that half of the lifespan of the blades gets reduced due to small temperature difference by improper cooling [3,6,9]. The specific damages are: blade trailing-edge cracks [8], buckling and risk of blade failure [11], thermal-fatigue [8,10,11]. Hence the perfect cooling is insisted for avoiding them. Many studies were conducted on optimization of lip thickness to slot height ratio (t/H) in trailing edge cooling of blades and vanes [12 -17] in which Kacker et al. [12,13] considered lip thickness constant to estimate film cooling effectiveness, Taslim et al [14,15] varies slot geometries and blowing ratios. The t/H ratio from 0.5 to 1, decrease the overall film-cooling effectiveness by about 10% [14-16]. The decreases of t/H ratio, increases the film-cooling effectiveness [17-19]. [20] considered a a rectangular divergent channel which consists of serpentine shape with ribs, dimples/protrusions, guide vanes, and pin fins at the tip turning the region for his heat transfer studies. [21] studied the cooling performance at tip surfaces of guide vanes and blades at turning regions and insisted the importance of proper design to obtaining desired effects. [22] recommended installing guide vanes in the tip turning regions most suitable way to improve cooling of tip surfaces. [23] insisted that selection appropriate cooling technique with respect to Figure 1: Fixed blade (Guide vane) configuration is must. The authors suggested two pass channels cooling at moving blades. This research work investigates with materials behaviors at elevated temperature for impingement cooling design on gas turbine fixed blade (guide vane). The Pro-E and ANSYS are employed to design and analysis. ANSYS is generally the preferred tool for analyzing structural stability. [24] used CATIA and ANSYS to design and investigate the structural stability of various components of Two-Wheeled Inverted Pendulum. In later [25] investigated the suitability of Kevlar29/epoxy composite for drive shaft. The influences of Paper ID: ART20173936 127