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Effect of Blade Deflection Angles, Pressure Drop, Flow and Work Co-Efficients on Stage Performance of a Gas Turbine Shrouded HP Compressor Blade

[+] Author Affiliations
Vinayaka Nagarajaiah, Nilotpal Banerjee

National Institute of Technology Durgapur, West Bengal, India

B. S. Ajay Kumar

Bangalore Institute of Technology, Bangalore, India

Kumar K. Gowda

Vivekananda Institute of Technology, Bangalore, India

Paper No. POWER2016-59328, pp. V001T02A004; 11 pages
doi:10.1115/POWER2016-59328
From:
  • ASME 2016 Power Conference collocated with the ASME 2016 10th International Conference on Energy Sustainability and the ASME 2016 14th International Conference on Fuel Cell Science, Engineering and Technology
  • ASME 2016 Power Conference
  • Charlotte, North Carolina, USA, June 26–30, 2016
  • Conference Sponsors: Power Division, Advanced Energy Systems Division, Solar Energy Division, Nuclear Engineering Division
  • ISBN: 978-0-7918-5021-3
  • Copyright © 2016 by ASME

abstract

In this paper a methodology for stage performance analysis of an axial flow compressor is carried out. A 1D/2D simulation based on Aero-thermodynamics is used to study the on and off-design performance of the HP compressor. Performance curves are obtained by changing the performance parameters in terms of design parameters like blade deflection angles, pressure drop, flow and work co-efficient’s, diffusion factor, solidity and Mach number. Results show the effect of diffusion factor on increasing efficiency than that of solidity and also the effect of both diffusion factor and solidity in increasing the amount of compression and compressor efficiency. Highest efficiency was found at the mean line between the root and tip of the blade. Best compressor efficiency is found at outlet metal angle in the range 51° to 55°. It was found that at hot section, HP compressor blades typically fail because of creep. Creep occurred as components are operated under high stresses and temperature over a time period. As per thumb rule (>15°C), i.e 20°C to 25°C increase in blade temperature if observed cuts creep life by 50%. Creep strain is of prime importance, because it leads to progressive reduction of rotor tip clearances causing axial and radial blade tip rubs, calling for fixity of shrouds at the rotor HP blade tip. Creep behavior in rotor HP blades are analyzed effectively by use of Industrial best practice like Larson Miller Parameter diagram.

Copyright © 2016 by ASME

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