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Thermo Mechanical Analysis of the Gas Turbine Blade


Affiliations
1 Mechanical Engineering Department, Motilal Nehru National Institute of Technology Allahabad, Prayagraj, U.P, India
     

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Gas turbine engines are extensively used in aerospace and power generation plants. In the gas turbine engine, the turbine blade is one of the most vital components. It is subjected to very complex loading conditions at high temperature along with high centrifugal and pressure load. The performance and life of the gas turbine engine mostly depends on the gas turbine blades. In this study, a single crystal Ni-based superalloy (CMSX-4) is used as the material of a twisted gas turbine blade. Two different models of gas turbine blades have been created. One of those is uncooled blade and other is blade with cooling channels of constant cross-section along the span length. Both the models have been used for steady state CFD analysis to get temperature, pressure, and heat transfer coefficient distribution on the blade surface. From CFD results, transient heat transfer analysis was performed to get temperature distribution in the blade. The temperature distribution obtained from heat transfer analysis along with centrifugal and pressure load is considered for transient thermo-mechanical analysis of the blade. In transient thermo-mechanical analysis maximum stress for model 1 and model 2 is 399.2 MPa and 380.8 MPa respectively.

Keywords

Gas Turbine Blade, CATIA, CMSX-4, CFD, Presser and Temperature, FEA, Abaqus.
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  • Abu, A,O., Samir, E., Laskaridis, P., & Riti, S. (2014). Aero-engine turbine blade life assessment using the Neu/Sehitoglu damage model. International Journal of Fatigue, 61, 160–169. 10.1016/j.ijfatigue.2014.11.015.

  • Wilson, D.G. (1984). Design of High-Efficiency Turbo machinery and Gas Turbines (1st ed). MIT Press.

  • Eggart, J., & Thompson, C.E. (2014). Heavy Duty Gas Turbine Operating and Maintenance Considerations. GE Gas Turbine.

  • Abu A.O., (2013). Integrated approach for stress based lifting of aero gas turbine blades. Cranfield University.

  • Zhuang, W.Z., & Swansson, N.S. (1998). Thermomechanical fatigue life prediction: A critical review (DSTO-TR-0609). DSTO Aeronautical Maritime Research Laboratory.

  • Luo, J., & Razinsky, E.H. (2007). Conjugate Heat Transfer Analysis of a Cooled Turbine Vane Using the V2F Turbulence Model. Journal of Turbomachinery, 129(4), 773-781.

  • Hylton, L.D., Mihelc M.S., Turner E.R., Nealy, D.A., & York, R.E. (1983). Analytical and Experimental Evaluation of the Heat Transfer Distribution Over the Surfaces of Turbine Vanes (19830020105). NASA Lewis Research Center.

  • Reyhani, M.R., Alizadeh, M., Fathi, A., & Khaledi, H. (2013). Turbine blade temperature calculation and life estimation - a sensitivity analysis. Propulsion and Power Research, 2(2), 148–161.

  • Cengel, Y.A., & Cimbala, J.M., Refrigeration and Air conditioning. McGraw-Hill Series in Mechanical Engineering.


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  • Thermo Mechanical Analysis of the Gas Turbine Blade

Abstract Views: 215  |  PDF Views: 0

Authors

Ganesh
Mechanical Engineering Department, Motilal Nehru National Institute of Technology Allahabad, Prayagraj, U.P, India
K. N. Pandey
Mechanical Engineering Department, Motilal Nehru National Institute of Technology Allahabad, Prayagraj, U.P, India
Devendra Pratap Singh
Mechanical Engineering Department, Motilal Nehru National Institute of Technology Allahabad, Prayagraj, U.P, India

Abstract


Gas turbine engines are extensively used in aerospace and power generation plants. In the gas turbine engine, the turbine blade is one of the most vital components. It is subjected to very complex loading conditions at high temperature along with high centrifugal and pressure load. The performance and life of the gas turbine engine mostly depends on the gas turbine blades. In this study, a single crystal Ni-based superalloy (CMSX-4) is used as the material of a twisted gas turbine blade. Two different models of gas turbine blades have been created. One of those is uncooled blade and other is blade with cooling channels of constant cross-section along the span length. Both the models have been used for steady state CFD analysis to get temperature, pressure, and heat transfer coefficient distribution on the blade surface. From CFD results, transient heat transfer analysis was performed to get temperature distribution in the blade. The temperature distribution obtained from heat transfer analysis along with centrifugal and pressure load is considered for transient thermo-mechanical analysis of the blade. In transient thermo-mechanical analysis maximum stress for model 1 and model 2 is 399.2 MPa and 380.8 MPa respectively.

Keywords


Gas Turbine Blade, CATIA, CMSX-4, CFD, Presser and Temperature, FEA, Abaqus.

References