Akshaya T. Poojary ¹, Rahul S. Sharma ², Meet H. Patel ³, Dharmik U. Sheth ⁴, Chandrakant R. Kini ¹, Rajesh Nayak ¹

Affiliations
1 Mechanical and Manufacturing Department, Manipal Institute of Technology, Manipal University, Manipal - 576104, Karnataka, IN
2 Mechanical Engineering, All India Shri Shivaji Memorial Society's (AISSMS) COE, Pune - 411001, Maharashtra, IN
3 Mechanical Engineering, Yadavrao Tasgaonkar Institute of Engineering and Technology (YTIET), Mumbai - 410201, Maharashtra, IN
4 Mechanical Engineering, Vidyavardhini College of Engineering and Technology, Mumbai - 401202, Maharashtra, IN

Abstract

Pressure vessels are widely used in industries for processing and storing fluids which are at different temperature and pressure in analogous to ambient. The design of these pressure vessels become the most paramount factor as any discrepancy would cause the vessel to explode, leading to injure many humans and failure of the setup. This paper designs the pressure vessel according to the pressure vessel handbook for both hemispherical and flat dish end pressure vessel so as to determine the most economic and efficient design. The various stresses engendered within the vessel were calculated and were learned to be within the permissible limits. The outer and inner diameter of the vessel was found to be 607mm and 480mm and the thickness of the vessel was determined to be 63.5mm. This design could withstand an internal pressure and temperature of 150psi and 500°F. The dimensions obtained from the design were further used to model both hemispherical and flat dish end pressure vessel with help of CAD in Catia V5R19.

Keywords

Design and Three Dimensional Modelling, Flat Dish End Pressure Vessel, Hemispherical Dish End Pressure Vessel

Full Text

   

Chandrakant R. Kini ¹, Sai Sharan Yalamarty ¹, Royston Marlon Mendonca ¹, N. Yagnesh Sharma ¹, B. Satish Shenoy ²

Affiliations
1 Department of Mechanical and Manufacturing Engineering, Manipal Institute of Technology, Manipal University, IN
2 Department of Aeronautical and Automobile Engineering, Manipal Institute of Technology, Manipal University, IN

Abstract

Gas turbines play a vital role in the today’s industrialized society, and as the demands for power increase, the power output and thermal efficiency of gas turbines must also increase. Modern high-speed aero-engines operate at elevated temperatures about 2000 K to achieve better cycle efficiencies. The internal cooling techniques of the gas turbine blade includes: jet impingement, rib turbulated cooling, and pin-fin cooling which have been developed to maintain the metal temperature of turbine blades within acceptable limits. Cooling passages having fins are incorporated into the trailing edge regions which are modelled and analysed to achieve maximum thermal performance in terms of cooling. It is seen that fins provide an augmented convective area for better heat dissipation. The shape and orientation of fins plays a major role in air flow patterns and greatly affects the heat dissipation rate.

Keywords

CHT Analysis, Fins, HP Stage Turbine, Trailing Edge Cooling

Full Text

   

Chandrakant R. Kini ¹, Harishkumar Kamat ¹, B. Satish Shenoy ²

Affiliations
1 Department of Mechanical and Manufacturing Engineering, Manipal Institute of Technology, Manipal University, Manipal – 576104, Karnataka, IN
2 Department of Aeronautical and Automobile Engineering, Manipal Institute of Technology, Manipal University, Manipal – 576104, Karnataka, IN

Abstract

Objectives: In gas turbine blades, heat transmission can be improved by using twisted tape inserts. In the present paper, cooling effect of a gas turbine blade can be improved by using suitable twisted tape configurations. Methods/Statistical Analysis: It was found from validation test that the twisted tape is a favourable technique for heat transfer augmentation. It was also found that heat transfer can be enhanced in the cases with suitable width ratio of twisted tapes. CFD Results show that the results are satisfactory when compared with the reference journal paper. Simulations are carried out for different width ratios of twisted tape inserts. Findings: Computation results showed that by employing twisted tape inserts of width ratio (W) = 0.3 provides better cooling effect compared to the others. The blade temperature is decreased by 34% at the leading edge. Application/Improvements: All these established that influence of cooling over gas turbine blade particularly at the leading edge can be enhanced with suitable twisted tape insert configurations.

Keywords

Leading Edge, Numerical Analysis, Turbine Blade Cooling, Twisted Tape Insert.

Full Text

   

Chandrakant R. Kini ¹, Harishkumar Kamat ¹, B. Satish Shenoy ²

Affiliations
1 Department of Mechanical and Manufacturing Engineering, Manipal Institute of Technology, Manipal University, Manipal – 576104, Karnataka, IN
2 Department of Aeronautical and Automobile Engineering, Manipal Institute of Technology, Manipal University, Manipal – 576104, Karnataka, IN

Abstract

Objectives: In gas turbine blades, heat transfer can be enhanced by using twisted tape inserts and stacks. In the present paper, we proposed cooling effect of a gas turbine blade can be improved by using suitable twisted tape inserts and stack configurations. A Comparative study between this type and the twisted tape without stack configurations was performed. Methods/Statistical Analysis: Simulations are carried out for different width ratios of twisted tape with and without using stack configurations. Computation results showed that by using twisted tape inserts of width ratio (W) = 0.3 with stack configurations, provides better cooling effect compared to the others. Findings: Without using the stack Configurations, blade temperature is decreased by 34% at the leading edge and 21.2% at the trailing edge for W = 0.3. By using stack configurations, the blade temperature is decreased by 50.7% at the leading edge and 48% at the trailing edge for W = 0.3. Application/Improvements: All these demonstrated that cooling effect of gas turbine blade especially at the trailing edge can be enhanced with suitable twisted tape and insert and stack configurations.

Keywords

Leading Edge, Numerical Analysis, Stacks, Trailing Edge, Turbine Blade Cooling, Twisted Tape Inserts.

Full Text

   

Chandrakant R. Kini ¹, N. Yagnesh Sharma ¹, B. Satish Shenoy ²

Affiliations
1 Department of Mechanical and Manufacturing Engineering, Manipal Institute of Technology, Manipal University, Manipal - 576104, Karnataka, IN
2 Department of Aeronautical and Automobile Engineering, Manipal Institute of Technology, Manipal University, Manipal - 576104, Karnataka, IN

Abstract

By having helicoidal shape for the cooling passage, it is possible to provide more surface area for cooling per unit passage length. In addition to this, by providing turbulators within the helicoidal passages, it is possible to augment an increase in heat transfer from the blade surface to the cooling fluid. Since FSI is the objective of this analysis, the blade loading corresponding to the static pressure as well as temperature field on the blades surfaces are obtained using CFD run. The output results are then used as structural boundary condition to solve FSI, using finite element method. The present work brings out thermal and structural distortion of the HP stage gas turbine blade. A parametric approach is used for varying the cooling passage geometry to optimize the cooling process. It can be concluded from FSI analysis that circular helicoidal cooling passage (4 mm Φ) of pitch 6 mm with turbulators of size e/D = 0.08 with rib thickness 0.75mm effect in improved cooling properties and in turn reduce structural deformation.

Keywords

Gas Turbine Blade Cooling, Helicoidal Passages, Turbulators, Thermo-Structural Investigation.

Full Text