Gas Turbine Internal Blade Cooling Study

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.