Gas Turbine Internal Blade Cooling Study

• Main Author: Mohd Hazran bin Mat Rahim, Mohd Hazran
• Format: Final Year Project
• Language: English
• Published: Universiti Teknologi Petronas 2010
• Subjects: TJ Mechanical engineering and machinery
• Online Access: http://utpedia.utp.edu.my/1415/1/GAS_TURBINE_INTERNAL_BLADE_COOLING_STUDY.pdf; http://utpedia.utp.edu.my/1415/

Gas Turbine engine is the engine that converts the energy of the moving stream of fluid into mechanical energy. It consists of four stages of the following four processes which are compression, combustion, expansion and exhaust. In expansion stage, hot gas expands across the turbine rotors. In this stage, the power turbine blades after the combustion chamber are located at very high pressure and temperature condition. This condition can affect and damage the strength, material and structure of the power turbine blade. The purpose of the project is to investigate and analyze the temperature profile along the turbine blade surface and to study on the fluid flow and heat transfer distribution of the turbine blade during the internal cooling process. It is important to ensure proper cooling can be performed. The scopes of study of the project are modeling the turbine blade, simulation of the model using ANSYS and ANSYS FLUENT, validation using publishes data by excluding the physical experiment and sensitivity study to look on the effect of the number and size of the holes and also effect on the types of hole of the turbine blade in the simulation. This project is done into several stages of process. Research and data collection is conducted for the system and the design of the blade. Then, the design and analysis of the turbine blade is carried up with software such as CATIA, ANSYS and FLUENT. Once all the design and analysis meet the specification, the sensitivity study of the model is carried up to look on the effect of the number and size of the holes and also effect on the types of hole of the turbine blade. From the simulation and analysis, it is proves that the design with cooling channel affect the temperature distribution along the turbine blade. Then, the author observes the effect of the number and size of the holes and also effect on the types of hole of the turbine blade. From both of the sensitivity study, the results show the holes at the blade and increase of number of cooling channels will improve the efficiency of the engine better as the thermal growth along the blade is improved. That conclusion satisfied the gas turbine cooling concept.