A Theory of Rotating Stall of Multistage Axial Compressors: Part I—Small Disturbances

Moore, F. K.

doi:10.1115/1.3239565

Cited by 118 publications

(51 citation statements)

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“…Engineers usually associated the former with a part-span stall which results in a small performance drop, whereas they associate the latter with a full-span stall and a large drop in performance. Notably, the part-span rotating stall occurs typically in single blade rows [6] and usually leads to more complex disturbances in single-rotor or stage machines than in multistage compressors [3].…”

Section: Introductionmentioning

confidence: 99%

“…Researchers have studied the detection and analysis of these different forms of aerodynamic instabilities for several decades. Numerous studies have clarified the problem of rotating stall of axial fiow compressors and focus on multistage machines [1][2][3]. The earlier work of Emmons et al [4] was one of the first attempts to describe the mechanism underlying the propagation of rotating stall.…”

Section: Introductionmentioning

confidence: 99%

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Stall Inception, Evolution and Control in a Low Speed Axial Fan With Variable Pitch in Motion

Bianchi

Corsini

Mazzucco

et al. 2012

Journal of Engineering for Gas Turbines and Power

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Obtaining the right pitch in turbomachinery blading is crucial to efficient and successful operations. Engineers adjust the rotor's pitch angle to control the production or absorption of power. Even for low speed fans this is a promising tool. This paper focuses on the inception and the evolution of the flow instabilities in the tip region which drive the stall onset in low speed axial fans. The authors conducted an experimental study to investigate the inception patterns of rotating stall evolution at different rotor blade stagger-angle settings with the aim of speculating on stable operating margin. The authors drove the fan to stall at the design stagger-angle setting and then operated the variable pitch mechanism in order to recover the unstable operation. They measured pressure fluctuations in the tip region of the low-speed axial-flow fan fitted with a variable pitch in motion mechanism, with flush mounted probes. The authors studied the flow mechanisms for spike and modal stall inceptions in this ¡Qw-speed axial-flow fan which showed relatively small tip clearance. The authors cross-correlated the pressure fluctuations and analyzed the crossspectra in order to clarify blade pitch, end wall flow, and tip-leakage flow influences on stall inception during the transient at the rotor blades' different stagger-angle settings. The authors observed a rotating instability near the maximum pressure-rise point at both design and low stagger-angle settings. The stall inception patterns were a spike type at the design stagger-angle setting as a result of the interaction between the incoming flow, tip-leakage flow and end wall backflow.

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Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Stall Inception, Evolution and Control in a Low Speed Axial Fan With Variable Pitch in Motion

Bianchi

Corsini

Mazzucco

et al. 2012

Journal of Engineering for Gas Turbines and Power

View full text Add to dashboard Cite

show abstract

“…The derivation of (1) and the analysis of transient behaviour including the dynamic pressure rise can be found in [11,12].…”

Section: Compressor Systemmentioning

confidence: 99%

Dynamic Modelling and Control of a Compressor Using Chebyshev Polynomial Approximation

Zagórowska

Thornhill

Skourup³

2018

Volume 6: Ceramics; Controls, Diagnostics, and Instrumentation; Education; Manufacturing Materials and Metallurgy

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The aim of this study is to apply a Chebyshev polynomial approximation of the compressor map for dynamic modelling and control of centrifugal compressors. The results are compared to those from an approximation based on the third order polynomials and a compressor map derived from first principles. In the analysis of centrifugal compressors, a combination of dynamic conservation laws and static compressor map provides an insight into the surge phenomenon, whose avoidance remains one of the objectives of compressor control. The compressor maps based on the physical laws provide accurate results, but require a detailed knowledge about the properties of the system, such as the geometry of the compressor and gas quality. Third order polynomials are usually used as an approximation for the compressor map, providing simplified models at the expense of accuracy. Chebyshev polynomial approximation provides a trade-off between the accuracy of physical modelling with the ease of use provided by third order polynomial approximation.

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“…Historically, in order to provide a simple yet effective model to predict stability margin of a compressor with inlet distortion, many efforts including various small perturbation theories [1] , parallel compressor models [2] , actuator disk theories [3] , and Moore-Greitzer based inertia parameter models [4][5] have been made. Longley et al [6] studied several multistage low-speed compressors with various RID and concluded that the excitation-and-response theory based on the 2D H-G model matched nicely with the test results of those compressors that exhibited only one peak in the response curve of stall margin shift versus distortion rotation speed, but failed to make a good agreement with those machines which had two peaks in the same kind of response curve.…”

Section: Introductionmentioning

confidence: 99%

The role of tip leakage flow in triggering rotating stall of a low speed compressor under inlet distortion

et al. 2009

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The stall behavior in a single-stage low-speed axial compressor under rotating inlet distortion (RID) is investigated in the first half of this paper. The tests demonstrate that the tip leakage flow (TLF) plays an important role in triggering rotating stall. The tracking of the spike-like disturbances caused by the spillage of TLV indicates that most of such spike-like disturbances will be smeared by non-distorted sector and the growth of the spike-like disturbances actually relate closely to how and how often the path of the propagating disturbances come across the path of the rotating distorted sector. In the second half of this paper, micro air injections are applied to test the effect behavior of TLF on stall inception. Contrasts to without micro air injections, the spike-like disturbances are much fewer, so the possibilities that spike-like disturbances may trigger rotating stall are fewer too. As a result, the compressor gets a lower mass flow rate at stall for both co-rotating inlet distortion and counter-rotating inlet distortion.

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A Theory of Rotating Stall of Multistage Axial Compressors: Part I—Small Disturbances

Cited by 118 publications

References 0 publications

Stall Inception, Evolution and Control in a Low Speed Axial Fan With Variable Pitch in Motion

Stall Inception, Evolution and Control in a Low Speed Axial Fan With Variable Pitch in Motion

Dynamic Modelling and Control of a Compressor Using Chebyshev Polynomial Approximation

The role of tip leakage flow in triggering rotating stall of a low speed compressor under inlet distortion

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