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Structural and Conceptual Design Analysis of an Axial Compressor for a 100 MW Industrial Gas Turbine (IND100)

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DOI: 10.4236/wjm.2014.411033    5,935 Downloads   6,671 Views  


The structural design of the IND100 axial compressor requires a multistage interrelationship between the thermodynamic, aerodynamic, mechanical design and structural integrity analysis of the component. These design criteria, sometimes act in opposition, hence engineering balance is employed within the specified design performance limits. This paper presents the structural and conceptual design of a sixteen stage single shaft high pressure compressor of IND100 with an overall pressure ratio of 12 and mass flow of 310 kg/s at ISOSLS conditions. Furthermore, in order to evaluate the conceptual design analysis, basic parameters like compressor sizing, load and blade mass, disc stress analysis, bearings and material selections, conceptual disc design and rotor dynamics are considered using existing tools and analytical technique. These techniques employed the basic thermodynamic and aerodynamic theory of axial flow compressors to determine the temperature and pressure for all stages, geometrical parameters, velocity triangle, and weight and stress calculations of the compressor disc using Sagerser Empirical Weight Estimation. The result analysis shows a constant hub diameter annulus configuration with compressor overall axial length of 3.75 m, tip blade speed of 301 m/s, maximum blade centrifugal force stress of 170 MPa, with major emphasis on industrial application for the structural component design selections.

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The authors declare no conflicts of interest.

Cite this paper

Aziaka, D. , Osigwe, E. and Lebele-Alawa, B. (2014) Structural and Conceptual Design Analysis of an Axial Compressor for a 100 MW Industrial Gas Turbine (IND100). World Journal of Mechanics, 4, 332-347. doi: 10.4236/wjm.2014.411033.


[1] Boyce, M. (2001) Gas Turbine Handbook. 2nd Edition, Gulf Professional Publishing, Houston.
[2] Saravanamuttoo, H., Rogers, G.F.C. and Cohen, H. (2001) Gas Turbine Theory. 5th Edition, Longman, London.
[3] Cumpsty, N.A. (1999) Compressor Aerodynamics. 5th Edition, Longman, London.
[4] Dixon, S.L. (2001) Fluid Mechanics and Thermodynamics of Turbomachinery. 5th Edition, Pergamon, UK.
[5] Funda, E. (2011) Multidisciplinary Conceptual Design of Transonic High Pressure Compressor. Master Thesis, Chalmers University of Technology Sweden, Sweden.
[6] Sagerser, D., Leiblein, S. and Krebs, R. (1997) Empirical Expression for Estimating Length and Weight of Axial Flow Component of VTOL Power Plants (Research Center, National Aeronautics Space Administration), United States of America. (Unpublished Technical Memorandum)
[7] GE (1994) GE Power Systems. GE, USA.
[8] Royce, B. (1997) Compressors Selection and Sizing. 2nd Edition, Gulf Publishing Company, Houston.
[9] Hanlon, P. (2001) Compressor Handbook. McGraw-Hill, New York.
[10] Jackson (2012) Engine Overall Structure. Cranfield University, Cranfield. (Unpublished Lecture Note)
[11] Haslam and Cookson, R.A. (2001) Mechanical Design of Turbomachinery. Cranfield University, Cranfield. (Unpublished Lecture Note)
[12] Ling, A.L. (2011) Compressor Selection and Sizing Guideline.
[13] Walsh, P.P. and Flectcher, P. (2004) Gas Turbine Performance. 2nd Edition, Blackwell Science, Oxford.
[14] Pilidis, P. (2012) Gas Turbine Theory and Performance. Cranfield University, Cranfield. (Unpublished Lecture Note)

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