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Performance Study of Novel Compressor Blades in a Two-Dimensional Cascade—Transonic Regime
- A. Vishwajeeth - PES University, Department of Mechanical Engineering, India ,
- Syeda Roquiya Badr - PES University, Department of Mechanical Engineering, India ,
- Nevin C. Cherian - PES University, Department of Mechanical Engineering, India ,
- Babu Rao Ponangi - PES University, Department of Mechanical Engineering, India ,
- K.S. Ravichandran - PES University, Department of Mechanical Engineering, India
Journal Article
01-15-01-0001
ISSN: 1946-3855, e-ISSN: 1946-3901
Sector:
Topic:
Citation:
Vishwajeeth, A., Badr, S., Cherian, N., Ponangi, B. et al., "Performance Study of Novel Compressor Blades in a Two-Dimensional Cascade—Transonic Regime," SAE Int. J. Aerosp. 15(1):3-18, 2022, https://doi.org/10.4271/01-15-01-0001.
Language:
English
Abstract:
Passengers would always like to reach their destinations with minimum commute
time. Generating a higher thrust is a necessity. This implies that the
turbomachinery associated with the power plant has to rotate faster and with
higher efficiencies. However, high rotational speeds, mainly in the transonic
regime, often lead to boundary layer separation, shocks, compressor stall, and
surge. The current investigation is an attempt to reduce the abovementioned
phenomena. It involves the performance study of a smoothened controlled
diffusion airfoil (CDA) blade that has been optimized by “Multi-Objective
Genetic Algorithm” (MOGA) by altering maximum camber location and stagger angle.
Inlet pressure is varied from 15 kPa to 30 kPa and the angle of attack ranging
from 40.4° to 56.4°. C48-S16-BS1 is validated and considered as the baseline
profile, and all other blades are collated to this. It is observed that shifting
the location of the maximum camber close to the leading edge and increasing
stagger angle result in improvement of blade performance in terms of lower
pressure losses for high angles of attack. Shifting the camber location slightly
lesser than the mid-chord and increasing the stagger angle showed the best
performance throughout. However, moving the camber location close to the
trailing edge always resulted in the highest amount of losses due to its poor
performance. Furthermore, a higher stagger angle is preferred.