Abstract
In order to improve compressor performance using a new design method, which originates from the fins on a humpback whale, experimental tests and numerical simulations were undertaken to investigate the influence of the tubercle leading edge on the aerodynamic performance of a linear compressor cascade with a NACA 65–010 airfoil. The results demonstrate that the tubercle leading edge can improve the aerodynamic performance of the cascade in the post-stall region by reducing total pressure loss, with a slight increase in total pressure loss in the pre-stall region. The tubercles on the leading edge of the blades cause the flow to migrate from the peak to the valley on the blade surface around the tubercle leading edge by the butterfly flow. The tubercle leading edge generates the vortices similar to those created by vortex generators, splitting the large-scale separation region into multiple smaller regions.
Funding statement: This study was supported by the National Science and Technology Major Project (2017-II-0004-0017).
Nomenclature
- Ma
Mach number
- L
length
- W
width
- H
height
- N
number of tubercle,=H/W
total pressure loss coefficient of cascade
- p*
total pressure
- p
static pressure
averaged total pressure
- Δ
relative value of total pressure loss coefficient change
- Subscript
- 1
inlet position of cascade
- 2
outlet position of cascade
- T
tubercle leading edge cascade
- O
original leading edge cascade
- Abbreviations
- AOA
angle of attack
- OLB
original leading edge blade
- TLB
tubercle leading edge blade
- OLC
original leading edge cascade
- TLC
tubercle leading edge cascade
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