Abstract
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.
Highlights
The IND100 is a single shaft industrial gas turbine with a recuperator delivering a shaft output power of 100 MW at a combustor exit temperature of 1600 K, overall pressure ratio of 12 and inlet air flow of 310 kg/s at 3000 rpm
The air stream moves in through the rotor blades, and the flow is later reduced in the stator blade passages whereas there is an increase in the pressure due to the shaft work done by the rotating blade which increases the total temperature and pressure, and there is continuous conversion of kinetic energy to static pressure by the rotor
The IND100 is a single shaft recuperated industrial gas turbine with sixteen stages of axial compressor and a VIGV with constant mean diameter annulus configuration, ten can-annular combustor, and four stages axial turbine with constant mean diameter annular configuration, operating with a combustor exit temperature of 1600 K, overall pressure ratio of 12, mass flow of 310 kg/s, 3000 rpm, and delivering 100 MW at ISOSLS conditions with generator coupled at the cold end drive
Summary
The IND100 is a single shaft industrial gas turbine with a recuperator delivering a shaft output power of 100 MW at a combustor exit temperature of 1600 K, overall pressure ratio of 12 and inlet air flow of 310 kg/s at 3000 rpm. The IND100 is a single shaft recuperated industrial gas turbine with sixteen stages of axial compressor and a VIGV with constant mean diameter annulus configuration, ten can-annular combustor, and four stages axial turbine with constant mean diameter annular configuration, operating with a combustor exit temperature of 1600 K, overall pressure ratio of 12, mass flow of 310 kg/s, 3000 rpm, and delivering 100 MW at ISOSLS conditions with generator coupled at the cold end drive
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