A Study of Spike and Modal Stall Phenomena in a Low-Speed Axial Compressor

Camp, Thomas R.; Day, I. J.

doi:10.1115/97-gt-526

Cited by 148 publications

(137 citation statements)

References 9 publications

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“…The researchers studying short wavelength disturbances refer to them as "spikes" or "pips" that are responsible for localised part-span stall cells [32][33][34][35]. The stall cell's spikelike inception in a single stage is clearly evident in data that researchers obtained from a model fan [36].…”

Section: Stall Inceptionmentioning

confidence: 99%

A Critical Review of Stall Control Techniques in Industrial Fans

Bianchi

Corsini

Sheard³

et al. 2013

ISRN Mechanical Engineering

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This paper reviews modelling and interpretation advances of industrial fan stall phenomena, related stall detection methods, and control technologies. Competing theories have helped engineers refine fan stability and control technology. With the development of these theories, three major issues have emerged. In this paper, we first consider the interplay between aerodynamic perturbations and instability inception. An understanding of the key physical phenomena that occurs with stall inception is critical to alleviate stall by design or through active or passive control methods. We then review the use of passive and active control strategies to improve fan stability. Whilst historically compressor design engineers have used passive control techniques, recent technologies have prompted them to install high-response stall detection and control systems that provide industrial fan designers with new insight into how they may detect and control stall. Finally, the paper reviews the methods and prospects for early stall detection to complement control systems with a warning capability. Engineers may use an effective real-time stall warning system to extend a fan's operating range by allowing it to operate safely at a reduced stall margin. This may also enable the fan to operate in service at a more efficient point on its characteristic.

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Section: Stall Inceptionmentioning

confidence: 99%

A Critical Review of Stall Control Techniques in Industrial Fans

Bianchi

Corsini

Sheard³

et al. 2013

ISRN Mechanical Engineering

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“…The rotating stall can be initiated in any stage of a multistage axial compressor, depending on geometrical factors and operating conditions, according to the experimental results of Camp and Day 3) and Day et al 4) In these cases, the simulation with a uniform axial velocity cannot be Ó 2011 The Japan Society for Aeronautical and Space Sciences applied directly to multi-stage axial compressors because the middle stages have severe inlet distortions both in radial and in circumferential directions. Although Smith 13) showed that the boundary layer thickness on the hub and casing increases moderately as the flow passes through each blade row in a multi-stage axial compressor, many researchers have used the clean inlet in the simulation of rotating stall, ignoring the effects of boundary layer thickness.…”

Section: Introductionmentioning

confidence: 99%

“…Referring to experimental results on the stall inception process, [1][2][3][4][5][6][7] the rotating stall follows modal perturbations with long-length scale or spiketype precursors with short-length scale, depending on the compressor operating conditions. In addition, it is also found that the rotating stall in an axial compressor originates from interactions between the tip leakage flow and the main flow.…”

Section: Introductionmentioning

confidence: 99%

Effects of Inlet Boundary Layer Thickness on Characteristics of Rotating Stall in Subsonic Axial Compressor

Choi

Chung

et al. 2011

Trans. Japan Soc. Aero. S Sci.

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A 3D numerical simulation was conducted to study the effect of inlet boundary layer thickness on rotating stall in an axial compressor. The inlet boundary layer thickness had significant effects on the hub-corner-separation at the corner of hub and suction surfaces. The hub-corner-separation grew considerably for a thick inlet boundary layer as the load increased, while it diminished to become indistinguishable from the rotor wake for a thin inlet boundary layer and another corner-separation originated near the casing. This difference in the internal flow near stall also had a large effect on characteristics of the rotating stall, especially the initial asymmetric disturbance and the size of stall cells. While a prestall disturbance arises firstly in the hub-corner-separation for the thick inlet boundary layer, an asymmetric disturbance was initially generated in the tip region because of the corner-separation for the thin inlet boundary layer. This disturbance was transferred to the tip leakage flow and grew to become an attached stall cell, which adheres to the blade passage and rotates at the same speed as the rotor. When this attached stall cell reached a critical size, it started moving along the blade row and became a short-length-scale rotating stall. The size of the stall cell for the thick inlet boundary layer was larger than for the thin inlet boundary layer. Due to the bigger size of the stall cell, the performance of the single rotor for the former case dropped more significantly than for the latter case.

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“…2) However, most studies on the rotating stall have been conducted using experiments focused on stall inception. [3][4][5][6][7][8][9] Generally, axial compressors have better performance near the stall point, but many stability problems arise near stall and surge points. Consequently, to operate compressors safely near the stall point and to control the rotating stall, it is necessary to understand rotating stall precursors.…”

Section: Introductionmentioning

confidence: 99%

Role of Hub-Corner-Separation on Rotating Stall in an Axial Compressor

Choi

Baek

et al. 2008

Trans. Japan Soc. Aero. S Sci.

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A 3D computation was conducted to investigate the role of hub-corner-separation on the rotating stall in a low-speed axial compressor. It is generally known that tip leakage flow plays an important role in stall inception. However, not much attention has been paid to the role of hub-corner-separation on the rotating stall although it is a common flow feature in an axial compressor operating near the stall point. During our time-accurate unsteady simulation, we suspected that hub-corner-separation might be a trigger for the rotating stall. After an asymmetric disturbance is initiated at hub-corner-separation, this disturbance is transferred to the tip leakage flows and grows to become an attached stall cell, which adheres to the blade passage and rotates at the same speed as the rotor. When the attached stall cell reaches a critical size, it moves along the blade row and becomes the rotating stall. The rotating speed of the stall cell decreases to 79% of the rotor so the stall cell rotates in the opposite direction to the rotor in the rotating frame.

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A Study of Spike and Modal Stall Phenomena in a Low-Speed Axial Compressor

Cited by 148 publications

References 9 publications

A Critical Review of Stall Control Techniques in Industrial Fans

A Critical Review of Stall Control Techniques in Industrial Fans

Effects of Inlet Boundary Layer Thickness on Characteristics of Rotating Stall in Subsonic Axial Compressor

Role of Hub-Corner-Separation on Rotating Stall in an Axial Compressor

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