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Frequency evaluation for mechanical integration of shrouded HP rotor blades in an aircraft engine compressor
Vinayaka, N1, Nilotpal Banerjee2, Ajay Kumar, B.S3, Kumar K. Gowda4, Suresh, P.M5.
Frequency evaluation in rotary engine blade design is an important research area
because of its critical applications in aircraft engines and land-based gas engines. A
compressor blade plays an important role in increasing pressure and velocity of the
fluid, which influences the efficiency of gas turbines. Due to peak centrifugal
stresses, gas bending loads and vibratory stresses, flow-induced blade vibrations
occur leading to blade catastrophe. The airfoil is expected to prove not only the
mechanical efficiency but also mechanical integrity for a desired life. The present
research focuses on the study of the vibrational behaviour of an Axial HP Shrouded
Compressor blade for in-service conditions. A Computational Fluid Dynamics
based model is generated with reference to NACA 65-series, to analyse the flow
behaviour through a linear cascade of axial compressor blades, followed by
mechanical integrity stress checks to take it further with root attachment design.
The present work demonstrates the need for shrouds in compressor rotor blades for
stiffening the blade to avoid resonance. The positioning of the shroud is a challenge
across the blade height by achieving Frequency Separation Margins using
Campbell Diagram, an industry best practice.
Affiliation:
- National Institute of Technology Durgapur, India
- National Institute of Technology Durgapur, India
- Bangalore Institute of Technology, India
- Vivekananda Institute of Technology, India
- ACS College of Engineering, India
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Indexed by |
MyJurnal (2019) |
H-Index
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0 |
Immediacy Index
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0.000 |
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Indexed by |
Scopus (SCImago Journal Rankings 2016) |
Impact Factor
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Rank |
Q3 (Engineering (miscellaneous)) |
Additional Information |
0.193 (SJR) |
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