22-10-2016, 09:24 AM
ABSTRACT:-
The objective of this project is to design and stresses analyze a turbine blade of a jet engine. An investigation for the usage of new materials is required. In the present work turbine blade was designed with two different materials named as Inconel 718 and Titanium T-6. An attempt has been made to investigate the effect of temperature and
induced stresses on the turbine blade. A thermal analysis has been carried out to investigate the direction of the temperature flow which is been develops due to the thermal loading. A structural analysis has been carried out to investigate the stresses, shear stress and displacements of the turbine blade which is been develop due to the coupling effect of thermal and centrifugal loads. An attempt is also made to suggest the best material for a turbine blade by comparing the results obtained for two different materials (Inconel 718 and titanium T6). Based on the plots and results Inconel718 can be consider as the
best material which is economical, as well as it has good material properties at higher temperature as compare to that of TitaniumT6.
I. INTRODUCTION
The gas turbine obtains its power by utilizing the energy of burnt gases and the air which is at high temperature and
pressure by expanding through the several rings of fixed and moving blades. The turbine drives the compressor so it is
coupled to the turbine shaft. After compression, the working fluid were to be expanded in a turbine, then assuming that
there were no losses in either component, the power developed by the turbine can be increased by increasing the volume of
working fluid at constant pressure or alternatively increasing the pressure at constant volume. Either of there may be done
by adding heat so that the temperature of the working fluid is increased after compression. To get a higher temperature of
the working fluid, a combustion chamber is required where combustion of air and fuel takes place giving temperature rise
to the working fluid. The turbine escapes energy from the exhaust gas. The present paper deals with the first type is
centrifugal stresses that act on the blade due to high angular speeds and second is thermal stresses that arise due to
temperature gradient within the blade material. The analysis of turbine blade mainly consists of the following two parts:
Structural and thermal analysis. The analysis is carried out under steady state conditions using ANSYS software. The study
has been conducted with two different materials Inconel 718 and Titanium T6.
II. LITERATURE SURVEY
V.Veeraragavan [5] had mainly done the research on the aircraft turbine blades; his main focus was on 10 C4/ 60 C50
turbine blades models. He had used the conventional alloys such as titanium, zirconium, molybdenum, and super alloys
were chosen for the analysis. He had analyzed the effect of the temperature on the different material for the certain interval
of times. And conclude the molybdenum alloys had better temperature resistance capability.
ISSN: 2319-8753
International Journal of Innovative Research in Science,
Engineering and Technology
Copyright to IJIRSET www.ijirset.com 13534
R D V Prasad, G Narasa Raju, M S S Srinivasa Rao, N Vasudeva Rao [7] had done research on different types of the cooling technique which maintain temperature of the blade to allowable limits, Finite element analysis is used to examine steady state thermal & structural performance for N155 & Inconel 718 nickel-chromium alloys. Four different
models consisting of solid blade and blades with varying number of holes (5, 9 & 13 holes) were analyzed to find out the optimum number of cooling holes. They had used two material Inconel 718 and Inconel 155 for their research work
and found out Inconel 718 has the better thermal properties as the blade temperature and the stress induce is lesser.
III. METHODOLOGY
1. Problem definition.
2. Calculate the dimensions of blade profile
3. Generate the 3-dimentional computer models
4. Prepare finite element model of the 3D computer model
5. Preprocess the 3D model for the defined geometry
6. Mesh the geometry model and refine the mesh considering sensitive zones for results accuracy
7. Post process the model for the required evaluation to be carried out
8. Determine maximum stress induced in blades.
9. Determine the temperature distribution along the blade profile.
10. Conclude the results.
The objective of this project is to design and stresses analyze a turbine blade of a jet engine. An investigation for the usage of new materials is required. In the present work turbine blade was designed with two different materials named as Inconel 718 and Titanium T-6. An attempt has been made to investigate the effect of temperature and
induced stresses on the turbine blade. A thermal analysis has been carried out to investigate the direction of the temperature flow which is been develops due to the thermal loading. A structural analysis has been carried out to investigate the stresses, shear stress and displacements of the turbine blade which is been develop due to the coupling effect of thermal and centrifugal loads. An attempt is also made to suggest the best material for a turbine blade by comparing the results obtained for two different materials (Inconel 718 and titanium T6). Based on the plots and results Inconel718 can be consider as the
best material which is economical, as well as it has good material properties at higher temperature as compare to that of TitaniumT6.
I. INTRODUCTION
The gas turbine obtains its power by utilizing the energy of burnt gases and the air which is at high temperature and
pressure by expanding through the several rings of fixed and moving blades. The turbine drives the compressor so it is
coupled to the turbine shaft. After compression, the working fluid were to be expanded in a turbine, then assuming that
there were no losses in either component, the power developed by the turbine can be increased by increasing the volume of
working fluid at constant pressure or alternatively increasing the pressure at constant volume. Either of there may be done
by adding heat so that the temperature of the working fluid is increased after compression. To get a higher temperature of
the working fluid, a combustion chamber is required where combustion of air and fuel takes place giving temperature rise
to the working fluid. The turbine escapes energy from the exhaust gas. The present paper deals with the first type is
centrifugal stresses that act on the blade due to high angular speeds and second is thermal stresses that arise due to
temperature gradient within the blade material. The analysis of turbine blade mainly consists of the following two parts:
Structural and thermal analysis. The analysis is carried out under steady state conditions using ANSYS software. The study
has been conducted with two different materials Inconel 718 and Titanium T6.
II. LITERATURE SURVEY
V.Veeraragavan [5] had mainly done the research on the aircraft turbine blades; his main focus was on 10 C4/ 60 C50
turbine blades models. He had used the conventional alloys such as titanium, zirconium, molybdenum, and super alloys
were chosen for the analysis. He had analyzed the effect of the temperature on the different material for the certain interval
of times. And conclude the molybdenum alloys had better temperature resistance capability.
ISSN: 2319-8753
International Journal of Innovative Research in Science,
Engineering and Technology
Copyright to IJIRSET www.ijirset.com 13534
R D V Prasad, G Narasa Raju, M S S Srinivasa Rao, N Vasudeva Rao [7] had done research on different types of the cooling technique which maintain temperature of the blade to allowable limits, Finite element analysis is used to examine steady state thermal & structural performance for N155 & Inconel 718 nickel-chromium alloys. Four different
models consisting of solid blade and blades with varying number of holes (5, 9 & 13 holes) were analyzed to find out the optimum number of cooling holes. They had used two material Inconel 718 and Inconel 155 for their research work
and found out Inconel 718 has the better thermal properties as the blade temperature and the stress induce is lesser.
III. METHODOLOGY
1. Problem definition.
2. Calculate the dimensions of blade profile
3. Generate the 3-dimentional computer models
4. Prepare finite element model of the 3D computer model
5. Preprocess the 3D model for the defined geometry
6. Mesh the geometry model and refine the mesh considering sensitive zones for results accuracy
7. Post process the model for the required evaluation to be carried out
8. Determine maximum stress induced in blades.
9. Determine the temperature distribution along the blade profile.
10. Conclude the results.