The Effects of Radially Distorted Incident Flow on Performance of Axial-Flow Fans With Forward-Skewed Blades

Yang, Bo; Gu, Ch. G.

doi:10.1115/1.4006535

Cited by 9 publications

(3 citation statements)

References 11 publications

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“…In this study, a commercial software CFX-Solver was used to solve the unsteady Reynolds-averaged Navier-Stokes equations with the help of SST k-ω turbulence model [19,20]. The second-order backward Euler scheme and the high-resolution scheme were adopted to discretize the temporal term and the convection terms, respectively.…”

Section: Computational Schemementioning

confidence: 99%

Impacts of Inlet Circumferential Distortions on the Aerodynamic Performance of a Transonic Axial Compressor

Yang

Zhu

2023

Processes

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Distortion, such as total pressure distortion, is a common phenomenon at the inlet of an axial compressor. Nonuniform inflow can greatly affect the aerodynamic performance and the stability of the compressor. In this paper, a sinusoidal distortion model is used at the inlet. Then, a series of unsteady computational fluid dynamics (CFD) simulations with a full-annulus model is conducted. Three kinds of the total pressure distortions, such as circumferentially covering 60, 120, and 180-degs sectors above 70% span of the blade at the inlet section, are adopted. Based on the results, how the rotating stall cells can be induced and developed under the different inlet conditions is understood during the stall process. It is found that the secondary stall cell is more easily triggered when the circumferential range of total pressure distortion is increased. Meanwhile, the influence of the rotating distortion on the compressor performance is also studied and a dangerous distortion rotating speed is observed.

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Section: Computational Schemementioning

confidence: 99%

Impacts of Inlet Circumferential Distortions on the Aerodynamic Performance of a Transonic Axial Compressor

Yang

Zhu

2023

Processes

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“…Gunn et al [28] investigated the effect of circumferential distortion on a fan stage operating at low speeds, reporting significant efficiency losses as a result of the large incidences on the blades along the entire annulus. A study on an axial fan with radial distortion blades identified that the modal waves leading to stall had a significant effect due to the flow near the hub region [29] . A few recent works have analyzed the characteristics of a high-aspect-ratio CRAF under radial and circumferential distortions [30,31] .…”

Section: Introductionmentioning

confidence: 99%

Influence of distorted inflows on the performance of a contra-rotating fan

Manas

Pradeep

2020

Aeronaut. j.

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A contra-rotating fan offers several aerodynamic advantages that make it a potential candidate for future aircraft engine configurations. Stall in a contra-rotating axial fan is interesting since instabilities could arise from either or both of the rotors. In this experimental study, a contra-rotating axial fan is analysed under clean or distorted inflow conditions to understand its performance and stall inception characteristics. The steady and unsteady measurements identified the relative contribution of each rotor towards the performance of the stage. The tip of rotor-1 is identified to be the most critical region of the contra-rotating fan. The contribution of rotor-2 to the overall loading of the stage is observed to be relatively less than rotor-1. The penalty due to distortion in the stage pressure rise is mostly felt by rotor-1, while rotor-2 also shows a reduction in performance for distorted inflows. Rotor-2 stalls at a high flow coefficient marking the initiation of partial stall of the stage, and the stall of the whole stage occurs once rotor-1 stalls. A fluid phenomenon that is attached to the blade surface marks the stall of rotor-1, and this fluid phenomenon initially rotates at a speed close to the speed of rotation of the blade. As the stage moves towards the fully developed stall, this fluid phenomenon sheds from the blade surface. The fluid phenomenon thus propagates at a speed much lower than the rotational speed of the blade during fully developed stall.

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“…Chima [8] has computationally studied the performance of NASA stage 35 using a 3D unsteady code and found that the performance agreed well with the experimental results with radial distortion and shows reduction in the stable flow range of the compressor. Yang and Gu [9] have conducted experimental and computational investigations to evaluate the effects of radially distorted incident flow on the performance of an axial flow fan with three kinds of forwarded-skewed blades. The results reveal the beneficial effect of forward-skewed blade on the performance.…”

Section: Introductionmentioning

confidence: 99%

Experimental Study of the Effect of Radially Distorted Inflow on a Contrarotating Fan Stage

Mistry

Pradeep

2014

International Journal of Rotating Machinery

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The paper reports results of a detailed study of hub-and tip-strong radial inflow distortion on the performance of a low speed, high aspect ratio (3.0) contrarotating fan stage. The distortion screen (placed upstream of the first rotor) covers 1/3 of the span of the blade near the hub and the casing for hub-strong and tip-strong inflow distortions, respectively. The performance of the contrarotating fan was investigated under both the radially distorted inflows and compared with the clean inflow conditions under different speed combinations of rotor-1 and rotor-2. The hub-strong radial distortion reduces the overall performance (pressure rise and efficiency) as well as the operating range by about 2 to 4% under the different speed combinations. On the other hand, it is interesting to observe that the tip covered radial distortion not only improves the pressure rise, but also increases the overall operating range by about 6 to 8%. There was, however, a 6 to 8% decrease in efficiency in this case as compared to 12 to 15% for hubstrong radial inflow distortion. The results reveal the physics of the effects of radial inflow distortion on the overall performance of the contrarotating fan stage.

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The Effects of Radially Distorted Incident Flow on Performance of Axial-Flow Fans With Forward-Skewed Blades

Cited by 9 publications

References 11 publications

Impacts of Inlet Circumferential Distortions on the Aerodynamic Performance of a Transonic Axial Compressor

Impacts of Inlet Circumferential Distortions on the Aerodynamic Performance of a Transonic Axial Compressor

Influence of distorted inflows on the performance of a contra-rotating fan

Experimental Study of the Effect of Radially Distorted Inflow on a Contrarotating Fan Stage

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