Aerodynamic Influence of Oscillating Adjacent Airfoils in a Linear Compressor Cascade

Keerthi, M. C.; Shubham, Shubham; Kushari, Abhijit

doi:10.2514/1.j055975

Cited by 13 publications

(11 citation statements)

References 20 publications

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“…Additionally, because the geometry of the reference cascade is span-wise uniform and meant to represent a blade section, the lift is not an accurate picture of the blade loading at the hub, which should be quantified with three-dimensional bladings. It is also worth noting that the choice of focusing on the pitching moment only and not on the lift is consistent with other works (see e.g., [2,23]). These works deal indeed with the unsteady aerodynamics and with the aeroelastic response of linear two-dimensional cascades.…”

Section: Results Of Traveling Wave Mode Simulationssupporting

confidence: 86%

“…It is found that the difference in lift, drag and moment coefficient falls below the fixed threshold already between the second and the third oscillation period. Notice that also Keerthi et al [2], who performed numerical computations on a cascade with pitching blades, found that their numerical solution reaches a good periodicity after two periods of oscillation. Namely, three oscillating cycles are simulated for small amplitude oscillations and four oscillating cycles for high amplitude oscillations are simulated in [2].…”

Section: Results Of Traveling Wave Mode Simulationsmentioning

confidence: 89%

“…Notice that also Keerthi et al [2], who performed numerical computations on a cascade with pitching blades, found that their numerical solution reaches a good periodicity after two periods of oscillation. Namely, three oscillating cycles are simulated for small amplitude oscillations and four oscillating cycles for high amplitude oscillations are simulated in [2]. Analogous results are obtained on the other two plasma-equipped blades of the cascade.…”

Section: Results Of Traveling Wave Mode Simulationsmentioning

confidence: 89%

“…Akcayoz et al [14] used the same solver and the same modeling to perform RANS computations on a compressor cascade equipped with plasma actuators, employed to control corner stall separations. Keerthi et al [2] used Ansys CFX R to carry out fully turbulent RANS computations closed with the k-ω SST Menter model on a linear cascade featuring blades oscillating in pitch.…”

Section: Ss Actuatormentioning

confidence: 99%

“…Natural consequences of these solutions are an aggressive blade loading and high flutter sensitivity, especially for long and slim blades. Fatigue phenomena, due to large vibratory loads, are severely enhanced [1,2]. Blade design approaches aiming specifically to provide a reduction in vibratory loads and a delay of the flutter onset were proposed, e.g., in Refs.…”

Section: Introductionmentioning

confidence: 99%

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Numerical Assessment of Virtual Control Surfaces for Load Alleviation on Compressor Blades

2018

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Virtual control surfaces for the optimization of steady and unsteady airloads on a compressor cascade are assessed numerically. The effects of mechanical surfaces are realized with plasma actuators, located both on the pressure and on the suction side of the blade trailing edge. Suction side plasma actuation is thought to reproduce the effects of mechanical wing spoilers, whereas pressure side plasma actuation is meant to act as a mechanical Gurney flap. Indeed, actuators are operated to generate an induced velocity field that is opposite relative to the direction of the freestream velocity. As a consequence, controlled recirculating flow areas are generated, which modify the effective mean line shape, as well as the position of the Kutta condition application point-and in turn the developed airloads. Proper triggering of pressure/suction side actuation is found to be effective in altering the blade loading, with effects comparable to those of mechanical control surfaces. Traveling wave mode simulations show that significant reductions in the peaks of the blade pitching moment can be achieved on the whole spectrum of interblade phase angles. It is proved that virtual control surfaces can provide effective load alleviation on the cascade, with potential remarkable reduction of fatigue phenomena.

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Section: Results Of Traveling Wave Mode Simulationssupporting

confidence: 86%

Section: Results Of Traveling Wave Mode Simulationsmentioning

confidence: 89%

Section: Results Of Traveling Wave Mode Simulationsmentioning

confidence: 89%

Section: Ss Actuatormentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Numerical Assessment of Virtual Control Surfaces for Load Alleviation on Compressor Blades

2018

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Reduced Order Modeling for Plasma Aeroelastic Control of Airfoils in Cascade: Dynamic Mode Decomposition

Neumann

Motta

Malzacher

et al. 2021

Notes on Numerical Fluid Mechanics and Multidisciplinary Design

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Impact of Additive Manufacturing Surface Roughness on the Aerodynamic Performance of Axial Compressor Blades

Lim,

Ko,

Hong

et al. 2024

Int. J. Aeronaut. Space Sci.

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This paper investigates the influence of additive manufacturing (AM) surface roughness on the aerodynamic performance of axial compressor blades. Though the AM offers advantages such as complex geometry fabrication and reduced material waste, its inherent surface roughness presents challenges in meeting compressor performance requirements. Previous studies have explored the implications of surface roughness on compressor performance. However, the existing literature on surface roughness does not sufficiently address the effects of AM surface roughness on the aerodynamic performance of compressor blades. Hence, in this paper, a linear compressor cascade experiment has been conducted at a Reynolds number $${Re}_{C}$$ Re C = 300,000. Three different roughness Reynold numbers, $${k}_{s}^{+}$$ k s + , have been examined—1.64 for the smooth blade, 24.5 and 43.8 for the rough 1 and rough 2 blades, respectively. Compared to the smooth blade, the pitchwise mass-averaged deviation and loss of the Rough 1 blade increase by 6.3% and 39.6%, respectively. For the Rough 2 blade, there is an increase of 18.4% and 98.8% in deviation and loss compared to the smooth blade, indicating a non-linear relationship between the deviation and loss, and $${k}_{s}^{+}$$ k s + .

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Aerodynamic Influence of Oscillating Adjacent Airfoils in a Linear Compressor Cascade

Cited by 13 publications

References 20 publications

Numerical Assessment of Virtual Control Surfaces for Load Alleviation on Compressor Blades

Numerical Assessment of Virtual Control Surfaces for Load Alleviation on Compressor Blades

Reduced Order Modeling for Plasma Aeroelastic Control of Airfoils in Cascade: Dynamic Mode Decomposition

Impact of Additive Manufacturing Surface Roughness on the Aerodynamic Performance of Axial Compressor Blades

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