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http://www.iaeme.com/IJMET/index.
International Journal of Mechanical Engineering and Technology (IJMET)Volume 8, Issue 5, May 2017, pp.
Available online at http://www.iaeme.com/IJM
ISSN Print: 0976-6340 and ISSN Online: 0976
© IAEME Publication
ANALYSIS OF GAS TURBINE BLADE
ASSEMBLY TO EVALUATE THE
PERFORMANCE OF VARIOUS NICKEL
Department Of Mechanical Engineering
MLR Institute o
ABSTRACT
The material selection plays a crucial step in the manufacturing and designing of
a rotor-turbine blade assembly. This paper summarizes the immense research over
three different turbine materials and an analysis is carried out to evaluate over few
drawbacks as well as positives of the considered metal alloys. Nickel based super
alloys are generally used for t
is carried out on the rotor-
deformation, displacement and Von
The results are compared
studied depending upon the material properties. CATIA V5, Analysis and Simulation
module is used for performing the present analysis. The current paper emphasizes on
the procedures of Analysis and co
quality and have a complete clarity about the material impacts over the turbine blade.
Keywords: Turbine Blade, CATIA, Nickel Based Alloys, Analysis
Cite this Article: P.Kezia, B.L.N.Krishna Sai Analysis of Gas Turbine Blade
Assembly to Evaluate the Performance of Various Nickel Based Alloys
Journal of Mechanical Engineering and Technology
http://www.iaeme.com/IJMET/issues.asp?JType=IJMET&VType=8&IType=5
1. INTRODUCTION
The complete procedures of design of a rotor blade assembly are summarized in the previous
work [1]. The extension of the work is proceeded by taking the materials into consideration.
These turbine blades are required to withstand large centrifugal forces, elevated temperatures
and are operated in aggressive environments. To survive in this difficult environment, turbine
blades often made from exotic materials. A key limiting factor in
performance of the materials available for the hot section of the engine especially the gas
turbine blades[2].When the same is undergone in thermal analysis, as the number of holes is
increases, the temperature distribution incr
IJMET/index.asp 665 [email protected]
International Journal of Mechanical Engineering and Technology (IJMET) 2017, pp. 665–673, Article ID: IJMET_08_05_073
http://www.iaeme.com/IJMET/issues.asp?JType=IJMET&VType=8&IType=5
6340 and ISSN Online: 0976-6359
Scopus Indexed
ANALYSIS OF GAS TURBINE BLADE
ASSEMBLY TO EVALUATE THE
PERFORMANCE OF VARIOUS NICKEL
BASED ALLOYS
P.Kezia, B.L.N.Krishna Sai
Department Of Mechanical Engineering,
Institute of Technology, Hyderabad, India.
The material selection plays a crucial step in the manufacturing and designing of
ssembly. This paper summarizes the immense research over
three different turbine materials and an analysis is carried out to evaluate over few
drawbacks as well as positives of the considered metal alloys. Nickel based super
alloys are generally used for the rotor blade manufacturing. Static structural analysis
-blade section for a particular working pressure to check the
deformation, displacement and Von-mises stresses for Inconel, Ni-Ti and Ni
The results are compared with each other and the performance characteristics are
studied depending upon the material properties. CATIA V5, Analysis and Simulation
module is used for performing the present analysis. The current paper emphasizes on
the procedures of Analysis and complete comparison of results so as to improve the
quality and have a complete clarity about the material impacts over the turbine blade.
Turbine Blade, CATIA, Nickel Based Alloys, Analysis.
P.Kezia, B.L.N.Krishna Sai Analysis of Gas Turbine Blade
Assembly to Evaluate the Performance of Various Nickel Based Alloys
Journal of Mechanical Engineering and Technology, 8(5), 2017, pp. 665
com/IJMET/issues.asp?JType=IJMET&VType=8&IType=5
The complete procedures of design of a rotor blade assembly are summarized in the previous
work [1]. The extension of the work is proceeded by taking the materials into consideration.
These turbine blades are required to withstand large centrifugal forces, elevated temperatures
and are operated in aggressive environments. To survive in this difficult environment, turbine
blades often made from exotic materials. A key limiting factor in gas turbine engines is the
performance of the materials available for the hot section of the engine especially the gas
[2].When the same is undergone in thermal analysis, as the number of holes is
increases, the temperature distribution increases [3]. Analysis is conducted over the turbine
T&VType=8&IType=5
ANALYSIS OF GAS TURBINE BLADE
ASSEMBLY TO EVALUATE THE
PERFORMANCE OF VARIOUS NICKEL
The material selection plays a crucial step in the manufacturing and designing of
ssembly. This paper summarizes the immense research over
three different turbine materials and an analysis is carried out to evaluate over few
drawbacks as well as positives of the considered metal alloys. Nickel based super
he rotor blade manufacturing. Static structural analysis
blade section for a particular working pressure to check the
Ti and Ni-Cr alloys.
with each other and the performance characteristics are
studied depending upon the material properties. CATIA V5, Analysis and Simulation
module is used for performing the present analysis. The current paper emphasizes on
mplete comparison of results so as to improve the
quality and have a complete clarity about the material impacts over the turbine blade.
P.Kezia, B.L.N.Krishna Sai Analysis of Gas Turbine Blade
Assembly to Evaluate the Performance of Various Nickel Based Alloys. International
65–673.
com/IJMET/issues.asp?JType=IJMET&VType=8&IType=5
The complete procedures of design of a rotor blade assembly are summarized in the previous
work [1]. The extension of the work is proceeded by taking the materials into consideration.
These turbine blades are required to withstand large centrifugal forces, elevated temperatures
and are operated in aggressive environments. To survive in this difficult environment, turbine
gas turbine engines is the
performance of the materials available for the hot section of the engine especially the gas
[2].When the same is undergone in thermal analysis, as the number of holes is
eases [3]. Analysis is conducted over the turbine
Analysis of Gas Turbine Blade Assembly to Evaluate the Performance of Various Nickel Based Alloys
http://www.iaeme.com/IJMET/index.asp 666 [email protected]
rotor blade unit taking into consideration the tangential inlet of gases over the turbine blade
with a pressure of 10 bar for three different materials. One of the research summarizes that the
Titanium alloy had the best performance[4].In other research carried out, it was marked for
Inconel 718 as best suitable for high temperature application [5], also based on the plots and
results of Inconel 718 was considered as the best material which is economical, as well as it
has good material properties at higher temperature as compare to that of Titanium T6 [6]. Al
2024 as well was termed as the best material in another research[7]. A similar work done on
Nickel alloys with graphite and coating with cobalt gave good results towards Thermal
analysis [8]. Hence a work is carried out on Nickel based alloys to estimate the material
performance.
2. METHODOLOGY
Modeling of the turbine blade as well as the rotor were modeled using surface modeling and
assembled in CATIA V5 which was elaborately shown in our previous paper [1]. A static
structural analysis determines the displacements, stresses, strains, and forces in structures or
components caused by loads that do not induce significant inertia and damping effects. Steady
loading and response conditions are assumed, that is, the loads and the structure's response are
assumed to vary slowly with respect to time. A static structural analysis is performed using
CATIA V5 software for the present work for which external pressures are applied. The
operating life of a turbine largely depends on the mechanical and chemical properties of the
materials used for turbine blades .Nickel based super alloys are generally used for the
manufacturing of the blades. Static analysis is performed for the performance of the rotor
blade assembly using three different alloys are done.
2.1. Static Analysis
Initially a new material as per the requirements is loaded to the material library by feeding the
material properties. Loaded material is assigned to the rotor blade assembly and the model is
dumped to Analysis and Simulation module. As the rotor is fixed to the shaft, the inner
diameter of the rotor is clamped as a fixed constraint, and the tangential pressure flow of 10
Bar is posed on to all the 16 turbine blades as shown in the Fig. 1. The deformations, Von
mises stresses and principal stresses are checked for the loading conditions.
Figure 1 Rotor Blade Assembly with constraints
2.2. Nickel-Chromium alloy (Inconel)
Analysis is performed on the above turbine blade assembly with the Inconel alloy as a
material and the deformation and stresses are as shown:
P.Kezia and B.L.N.Krishna Sai
http://www.iaeme.com/IJMET/index.asp 667 [email protected]
Figure 2 Von-Mises stresses for Inconel alloy
Figure 3 Translational displacement of Inconel alloy.
Analysis of Gas Turbine Blade Assembly to Evaluate the Performance of Various Nickel Based Alloys
http://www.iaeme.com/IJMET/index.asp 668 [email protected]
Figure 4 Principal stresses of Inconel alloy.
2.3. Nickel-Titanium alloy
Analysis is performed on the above turbine blade assembly with the Inconel alloy as a
material and the deformation and stresses are as shown:
Figure 5 Von-Mises stresses for Ni-Ti alloy.
P.Kezia and B.L.N.Krishna Sai
http://www.iaeme.com/IJMET/index.asp 669 [email protected]
Figure 6 Translational displacement of Ni-Ti alloy.
Figure 7 Principal stresses of Ni-Ti alloy.
2.4. Nickel-Copper alloy
Analysis is performed on the above turbine blade assembly with the Nickel-Copper alloy as a
material and the deformation and stresses are as shown:
Analysis of Gas Turbine Blade Assembly to Evaluate the Performance of Various Nickel Based Alloys
http://www.iaeme.com/IJMET/index.asp 670 [email protected]
Figure 8 Von-Mises stresses for Ni-Cu alloy
Figure 9 Translational displacement of Ni-Cu alloy.
Figure 10 Principal stresses of Ni-Cu alloy.
P.Kezia and B.L.N.Krishna Sai
http://www.iaeme.com/IJMET/index.asp 671 [email protected]
Table 1 Material Properties of the Nickel based alloys
S.No Material Ni – Cr Ni-Ti Ni- Cu
1 Young’s modulus 1.43e+011N_m2 8e+010N_m2 1.56e+011N_m2
2 Poisson’s ratio 0.344 0.33 0.34
3 Density 8249kg_m3 6450kg_m3 8860kg_m3
4 Yield strength 5.5e+008N_m2 6e+008N_m2 1.7e+008N_m2
5 Coefficient of thermal
expansion 1.77e+007_Kdeg 1.1e-005_Kdeg 25_Kdeg
3. RESULTS AND DISCUSSION
Table 2 Results of static analysis conducted for three different alloys
S.No. Material
Principal Stresses
(N-m^2)
Von Mises Stresses
(N-m^2) Displacement
(mm) Maximum Minimum Maximum Minimum
1 Ni – Cr 4.18e+006 -2.35e+006 4.49e+006 4.62e+004 0.00756
2 Ni-Ti 4.26e+006 -2.34e+006 4.61e+006 4.46e+004 0.00753
3 Ni- Cu 4.26e+006 -2.35e+006 4.49e+006 4.62e+004 0.00385
The analysis is performed by fixing the clamp or constraint at the mid portion of the
turbine as shown in Fig. 1. The basic meshing is taken as linear tetrahedron. The structure
computation is calculated with the fine mesh comprising of 25589 nodes and 104622
elements. The deformation of the rotor is negligible as the inner side of the rotor is fixed to
the shaft portion. As it is pure structural which depends upon the geometry as well as the
clamping, the deformation of the rotor is completely independent of the structure itself
whereas the translational displacement slightly depends upon the material used at the tip of
the blade exclusively. Hence the deformation of the blade unit as tabulated has the maximum
translational displacement value of 0.00756mm for the Ni-Cr alloy, whereas Ni-Cu has the
minimum displacement of 0.00385mm comparatively. Going further in the analysis, the
pressure of 10 bar is applied on to the 16 blades tangentially. The deformation, principal
stresses and Von mises stresses are calculated for the three different materials. The properties
of those materials are as tabulated in Table 1. Applied resultant load resultant for Ni-Cr, Ni-Ti
and Ni-Cu alloys is as follows:
Analysis of Gas Turbine Blade Assembly to Evaluate the Performance of Various Nickel Based Alloys
http://www.iaeme.com/IJMET/index.
The results of strain energy for Ni
Ni-Cu being 2.53e-003J and 1.279e
4. CONCLUSION
CATIA V5 which is a complete sophisticated suite, is completely utilized for the present
work which gives more efficient results and also saves time. As the
modeled in the CATIA software itself, it does not require any special formatting of the model
file instead it is directly used as is. The analysis was successfully carried out for the three
different alloys. The maximum
same and this principal stresses of maximum value is occurring at the joining of the blade
profile and the rotor, and is still under sustained condition. Maximum and
stress for Ni-Cr alloy is very close enough to the other two alloys showing almost the same
behavioral conditions. Looking at minimum principal stresses and it medieval values clearly
show that the rotor blade assembly is safe for the applied load. Comparing the Von
stresses of the turbine assembly under same working conditions for three materials which are
very close enough indicates that the values are lying between the maximum and minimum
values ranging from 4.49e+006 to 4.62e+004. Intense study of th
that the Ni-Ti and Ni-Cu alloy withstand better at the stress concentration areas of the blade
and rotor which is at the adjoining tip of the assembly. Translational displacement is very less
comparatively, the little displacement taking place is obser
of e-003 values. Among the three material turbine assemblies, the one with Ni
maximum displacement of 0.00756 and the least displacement being Ni
Ni-Cr alloy’s behaves better in terms of
comparatively though the translational displacement is more. Ni
good behavior which has a dominant low translational displacement and the Von
stresses being the same as that of Ni
REFERENCES
[1] P. Kezia, V. Ratna Kiran, Modeling and Analysis of a Turbine Blade,
110-117.
[2] V.Nagabhushana Rao, I.N.Niranjan Kumar, B.Vamsi Krishna, N.Madhulata, M.Anudeep,
Analytical Comparative Study Of Gas Turbine Blade Materials Used In Marine
Applications Using FEA Techniques,
Management Research
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Thermal Analysis on Gas Turbine Blade Using Solid Works,
Advanced Scientific Technologies in Engineering and
2(4),2016,pp. 5-8.
Analysis of Gas Turbine Blade Assembly to Evaluate the Performance of Various Nickel Based Alloys
IJMET/index.asp 672 [email protected]
Figure 11 Applied load resultant
The results of strain energy for Ni-Cr alloy is noted as 1.38e-003J and that of Ni
003J and 1.279e-003 respectively.
CATIA V5 which is a complete sophisticated suite, is completely utilized for the present
work which gives more efficient results and also saves time. As the rotor
modeled in the CATIA software itself, it does not require any special formatting of the model
file instead it is directly used as is. The analysis was successfully carried out for the three
different alloys. The maximum principal stresses obtained for Ni-Ti and Ni
same and this principal stresses of maximum value is occurring at the joining of the blade
profile and the rotor, and is still under sustained condition. Maximum and
very close enough to the other two alloys showing almost the same
behavioral conditions. Looking at minimum principal stresses and it medieval values clearly
show that the rotor blade assembly is safe for the applied load. Comparing the Von
of the turbine assembly under same working conditions for three materials which are
very close enough indicates that the values are lying between the maximum and minimum
values ranging from 4.49e+006 to 4.62e+004. Intense study of the Figures 2, 5 and 8
Cu alloy withstand better at the stress concentration areas of the blade
and rotor which is at the adjoining tip of the assembly. Translational displacement is very less
comparatively, the little displacement taking place is observed at the extreme tip of the blade
003 values. Among the three material turbine assemblies, the one with Ni
maximum displacement of 0.00756 and the least displacement being Ni-Cu alloy. Therefore
Cr alloy’s behaves better in terms of principal stresses and Von mises stresses are least
comparatively though the translational displacement is more. Ni-Cu alloy also has a fairly
good behavior which has a dominant low translational displacement and the Von
at of Ni-Cr.
P. Kezia, V. Ratna Kiran, Modeling and Analysis of a Turbine Blade,
V.Nagabhushana Rao, I.N.Niranjan Kumar, B.Vamsi Krishna, N.Madhulata, M.Anudeep,
Analytical Comparative Study Of Gas Turbine Blade Materials Used In Marine
Applications Using FEA Techniques, International Journal Of Engineering Sciences &
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Thermal Analysis on Gas Turbine Blade Using Solid Works, International Journal of
Advanced Scientific Technologies in Engineering and Management Sciences
Analysis of Gas Turbine Blade Assembly to Evaluate the Performance of Various Nickel Based Alloys
003J and that of Ni-Ti and
CATIA V5 which is a complete sophisticated suite, is completely utilized for the present
rotor-turbine blade is
modeled in the CATIA software itself, it does not require any special formatting of the model
file instead it is directly used as is. The analysis was successfully carried out for the three
Ti and Ni-Cu alloys are
same and this principal stresses of maximum value is occurring at the joining of the blade
profile and the rotor, and is still under sustained condition. Maximum and minimum principal
very close enough to the other two alloys showing almost the same
behavioral conditions. Looking at minimum principal stresses and it medieval values clearly
show that the rotor blade assembly is safe for the applied load. Comparing the Von-mises
of the turbine assembly under same working conditions for three materials which are
very close enough indicates that the values are lying between the maximum and minimum
e Figures 2, 5 and 8 shows
Cu alloy withstand better at the stress concentration areas of the blade
and rotor which is at the adjoining tip of the assembly. Translational displacement is very less
ved at the extreme tip of the blade
003 values. Among the three material turbine assemblies, the one with Ni-Cr shows the
Cu alloy. Therefore
principal stresses and Von mises stresses are least
Cu alloy also has a fairly
good behavior which has a dominant low translational displacement and the Von-mises
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V.Nagabhushana Rao, I.N.Niranjan Kumar, B.Vamsi Krishna, N.Madhulata, M.Anudeep,
Analytical Comparative Study Of Gas Turbine Blade Materials Used In Marine
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Management Sciences,
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