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Aero Structure Interaction for Mechanical Integration of Laced LP Compressor Blades in a Gas Engine Rotor

[+] 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. POWER2016-59319, pp. V001T10A003; 9 pages
doi:10.1115/POWER2016-59319
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

Aero-structure interaction during turbomachinery blade design has become an important area of research due to its critical applications in aero engines and land based gas turbines. Studies reveal that a certain mistuning leads to stress build up through mode localization under operating conditions. This paper deals with comparative case studies of aero-structure interaction for free standing and various laced LP blade configurations of a gas turbine. The lacing wire provides better structural integrity as it is more aerodynamic and feasible when compared to cases of free standing blades without lacing wires. Hence calling for the optimum positioning checks at ¼th, ½, ¾th and combined positioning at ¼th and ¾th along the length of LP compressor blades. The lacing wire of both circular and elliptical cross sections are considered for comparative study for better aerodynamic performance. Assuming 100% fixity at blade root, the study involves critical parametric evaluations involved in achieving mechanical integrity in airfoil design and blade platform design. Mechanical integrity involves stress checks, frequency margins, Campbell Diagram, gross yield stress, Stress Stiffening and Spin Softening of blades and so on, for design and off-design conditions for a given stage efficiency of 93% in an ideal LP compressor of a gas turbine engine.

Copyright © 2016 by ASME

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