Film Cooling of Turbine Rotor Blade

Over the past fifty years, aircraft and power generation gas turbine designers have endeavored to increase the cumbustor exit and high-pressure turbine stage inlet temperatures. With higher combustor exit temperatures, improved efficiency and reduced fuel consumption can be achieved. Similarly, in a

Project Title

Film Cooling of Turbine Rotor Blade

Project Area of Specialization

Mechatronics Engineering

Project Summary

Over the past fifty years, aircraft and power generation gas turbine designers have endeavored to increase the cumbustor exit and high-pressure turbine stage inlet temperatures. With higher combustor exit temperatures, improved efficiency and reduced fuel consumption can be achieved. Similarly, in aircraft application, the higher temperatures lead to increased thrust. Unfortunately, these higher temperatures have jeopardized the integrity of the high-pressure turbine components and specifically the turbine blades. Modern turbine stage inlet temperatures exceed the melting point temperatures of turbine blade materials. To combat and avert failure of turbine blades in gas turbine engines resulting from these excessive operating temperatures, film cooling has been incorporated into blade designs. In film cooling, cool air is bled from the compressor stage, ducted to the internal chambers of the turbine blades, and discharged through small holes in the blade walls. This air provides a thin, cool, insulating blanket along the external surface of the turbine blade.

Project Objectives

. Our objective of this project is to study the phenomena of film cooling on turbine blade using Ansy fluent and study different influencing factors of cooling such as holes geometry, injection angle, mass flow rate, Reynolds number, and turbulence and boundary layer thickness. Our objective of this project is to study the phenomena of cooling on turbine blade using Ansy fluent and study different influencing factors of cooling such as holes geometry, injection angle, mass flow rate, Reynolds number, and turbulence and boundary layer thickness

Project Implementation Method

Following is the procedure we adopt in our project:

1.Literature review to understand film cooling phenomenon

2.Read ASME(American Society of Mechanical Engineering) papers

3. Made geometry of Nozzle Guided vain and rotor

4.Run simulation on Ansys Fluent(Fluid analysis software)

Benefits of the Project

1.Turbine blade could withstand at very high temperature without melting

2.Highly efficent aircraft engine

3.Greater thrust and supersonic speed of aircrafts

4.No ceramic coating is require on turbine blade

5.Only the countries who managed to master film cooling have their own aircraft engines.

Technical Details of Final Deliverable

In this simulation based project,we will implement phenomenon of film cooling on willliam engine turbine blade.Our study will decide what are keys factors which effect film cooling and how to implement film cooling on turbine blade in a effective manner

Final Deliverable of the Project

Software System

Core Industry

Others

Other Industries

Core Technology

Others

Other Technologies

Sustainable Development Goals

Industry, Innovation and Infrastructure

Required Resources

If you need this project, please contact me on contact@adikhanofficial.com