analysis of gas turbine blade assembly to … · the material selection plays a crucial step in the...

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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




BASED ALLOYS

P.Kezia, B.L.N.Krishna Sai

Department Of Mechanical Engineering,

Institute of Technology, Hyderabad, India.


ssembly. This paper summarizes the immense research over



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



the procedures of Analysis and complete comparison of results so as to improve the


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





blades often made from exotic materials. A key limiting factor in gas turbine engines is the


[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

[email protected]

T&VType=8&IType=5





ssembly. This paper summarizes the immense research over



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



mplete comparison of results so as to improve the


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





gas turbine engines is the


[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


Figure 2 Von-Mises stresses for Inconel alloy

Figure 3 Translational displacement of Inconel alloy.



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


Figure 5 Von-Mises stresses for Ni-Ti alloy.



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




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.



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:


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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

[3] R.Mahesh, A.Sreekar Reddy, K.Lokesh, D.BabaFakruddin, D.Videetha

Thermal Analysis on Gas Turbine Blade Using Solid Works,

Advanced Scientific Technologies in Engineering and

2(4),2016,pp. 5-8.


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.


work which gives more efficient results and also saves time. As the rotor



different alloys. The maximum principal stresses obtained for Ni-Ti and Ni


profile and the rotor, and is still under sustained condition. Maximum and

very close enough to the other two alloys showing almost the same


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


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


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,


Applications Using FEA Techniques, International Journal Of Engineering Sciences &

rch, ISSN: 2349-6193, 2014,pp. 12-24.

R.Mahesh, A.Sreekar Reddy, K.Lokesh, D.BabaFakruddin, D.Videetha

Thermal Analysis on Gas Turbine Blade Using Solid Works, International Journal of

Advanced Scientific Technologies in Engineering and Management Sciences


[email protected]

003J and that of Ni-Ti and


rotor-turbine blade is



Ti and Ni-Cu alloys are


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


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


e Figures 2, 5 and 8 shows

Cu alloy withstand better at the stress concentration areas of the blade


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

P. Kezia, V. Ratna Kiran, Modeling and Analysis of a Turbine Blade, RIME-2014, pp.

V.Nagabhushana Rao, I.N.Niranjan Kumar, B.Vamsi Krishna, N.Madhulata, M.Anudeep,


International Journal Of Engineering Sciences &

R.Mahesh, A.Sreekar Reddy, K.Lokesh, D.BabaFakruddin, D.Videetha, Structural And

International Journal of

Management Sciences,



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2320-2092,3(7), 2015,pp. 62-66.

[5] R D V Prasad, G Narasa Raju, M S SSrinivasa Rao, N Vasudeva Rao, Steady State

Thermal & Structural Analysis Of Gas Turbine Blade Cooling System, International

Journal of Engineering Research & Technology, ISSN: 2278-0181, 2(1),2013, pp. 1-6.

[6] Theju V, Uday P S , PLV Gopinath Reddy , C.J.Manjunath, Design and Analysis of Gas

Turbine Blade, International Journal of Innovative Research in Science, Engineering and

Technology, ISSN: 2319-8753, 3(6), 2014,pp. 13533-13539.

[7] GollapothuBoyaraju, SanmalaRajasekhar, A.V Sridhar, J.Hari Narayana Rao, Thermal

Analysis Of A Gas Turbine Rotor Blade, International Journal of Science Engineering

and Advance Technology, ISSN 2321-6905,3(12), 2015, pp. 1181-1187.

[8] Nandish R.V, Madhu E, S. Paul Vizhian and S. Ramachandra, Dynamic Vibration

Analysis of Ti-Alloy Gas Turbine Blade Rotating at High Speed After Grind Out Repair

of Foreign Object Damage. International Journal of Mechanical Engineering and

Technology, 8(4), 2017, pp. 202–211.

[9] N. Suresh, T. L. Rakesh Babu, Analysis of Gas Turbine Blade for Different Materials,

International Journal of Scientific Engineering and Technology Research, ISSN 2319-

8885,3(45), 2014, pp. 9093-9097.

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