1997 Best Paper Award—Turbomachinery Committee: A Study of Spike and Modal Stall Phenomena in a Low-Speed Axial Compressor

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

doi:10.1115/1.2841730

Cited by 305 publications

(53 citation statements)

References 13 publications

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“…The second pattern begins with a long length-scale disturbance, which appears prior to the formation of a fully developed stall cell. This pattern is known as "modal stall inception" [1][2]. Another short length-scale disturbance, which does not lead directly to stall, has also been observed in low-speed compressors.…”

Section: Introductionmentioning

confidence: 98%

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Inception mechanism and suppression of rotating stall in an axial-flow fan

Nishioka

2013

IOP Conf. Ser.: Mater. Sci. Eng.

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Section: Introductionmentioning

confidence: 98%

“…The first inception pattern begins with a short length-scale stall cell. This pattern is known as "spike stall inception" [1][2]. The second pattern begins with a long length-scale disturbance, which appears prior to the formation of a fully developed stall cell.…”

Section: Introductionmentioning

confidence: 99%

Inception mechanism and suppression of rotating stall in an axial-flow fan

Nishioka

2013

IOP Conf. Ser.: Mater. Sci. Eng.

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“…The spike type, which sometimes occurs following the modal type, demonstrates an abrupt turbulence (usually an upward spike emerges in the transient pressure curve and a downward spike in velocity curve) and a more rapid circumferential speed than that of the modal type [8,9].…”

Section: Nomenclaturementioning

confidence: 96%

Experimental Investigation of Surge and Stall in a High-Speed Centrifugal Compressor

Zheng

Liu

2015

Journal of Propulsion and Power

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Flow instability, known as surge and stall, limits the stable operating range of compressors. In this paper, a panoramic map of instability evolution across all typical operations is experimentally demonstrated for the first time in a high-speed centrifugal compressor with a maximum speed of 185;000 r∕ min and a corresponding rotation velocity at the impeller outlet of 593 m∕s. Twelve high-response Kulite pressure probes are mounted on the internal surface of the compressor's casing. The experimental results show that the instability phenomena are quite complex and diverse at different operations. At low speed (<70% of the maximum speed), high-frequency and low-frequency stall successively occurs at the impeller, and is followed by surge as mass flow rate reduced. The transient process of surge is a transient stall/unstall self-loop, with the "self-similarity" to the sustainable stall/unstall conditions. At 70% of the maximum speed, the system exhibits two types of surge, a minor-amplitude periodic surge with a frequency close to the Helmholtz system resonance frequency, and a deep surge. There is a non-surge region between them. Meanwhile the 70% of the maximum speed is a critical speed, beyond which the stable flow range narrows down abruptly. When the compressor operates at near of the maximum speed, surge suddenly sets in from stable state and there is no preceding stall. Finally, a new "mass-spring-damper" model is introduced for the first time to illustrate the diversity of surge/stall patterns across different operations. NomenclatureA c = equivalent compressor duct area Ai = impeller inlet, where i is equal to 1, 2 a = averaged sound velocity B= non-dimensional parameter on Greitzer's theory Bi = impeller mid-span, where i is equal to 1, 2 C = compressor characteristic Ci = diffuser inlet, where i is equal to 1, 2, 3, 4 c = slope of compressor characteristic c p = specific heat capacity at constant pressure Di = diffuser mid-section, where i is equal to 1, 2, 3, 4 d c = equivalent diameter of the duct F = the friction loss factor F n = friction resistance loss f c = system oscillation frequency f H = Helmholtz frequency f r = rotor frequency G = throttle characteristic g = throttle characteristic slope k = specific heat ratio l c = equivalent length of the duct m = mass flow rate m r = nondimensional mass flow rate N = compressor rotational speed n = intersecting pipe number S c = compressor energy factor T = temperature T 01 = static temperature at impeller inlet t o = time length of a rotor revolution p = pressure p dR = reference dynamic pressure u 2r = radial velocity at impeller exit u rev = impeller tip velocity at specific speed u 2τ = tangential velocity at impeller exit V p = volume of the compressed air v 2x = axial velocity in the duct z = pressure or mass perturbation ζ = local resistance coefficient at intersecting pipe λ = frictional resistance coefficient ρ = air density ρ e = air density of ambient temperature φ = corresponding physical quantity Subscripts cri = critical value 0 = total pa...

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“…Resolving this challenge has been complicated by the broad range of conditions involved and by the presumed role of stall precursors. The latter could be classified as "modal," i.e., associated with large-scale initial flow disturbances, or "spiketype," namely, involving perturbations with short duration [18,19].…”

Section: Introductionmentioning

confidence: 99%

Visualization and Time-Resolved Particle Image Velocimetry Measurements of the Flow in the Tip Region of a Subsonic Compressor Rotor

Tan

Wilkes

et al. 2014

Journal of Turbomachinery

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A new optically index matched facility has been constructed to investigate tip flows in compressor-like settings. The blades of the one and a half stage compressor have the same geometry, but lower aspect ratio as the inlet guide vanes (IGVs) and the first stage of the low-speed axial compressor (LSAC) facility at NASA Glenn. With transparent blades and casings, the new setup enables unobstructed velocity measurements at any point within the tip region and is designed to facilitate direct measurements of effects of casing treatments on the flow structure. We start with a smooth endwall casing. High speed movies of cavitation and time-resolved PIV measurements have been used to characterize the location, trajectory, and behavior of the tip leakage vortex (TLV) for two flow rates, the lower one representing prestall conditions. Results of both methods show consistent trends. As the flow rate is reduced, TLV rollup occurs further upstream, and its initial orientation becomes more circumferential. At prestall conditions, the TLV is initially aligned slightly upstream of the rotor passage, and subsequently forced downstream. Within the passage, the TLV breaks up into a large number of vortex fragments, which occupy a broad area. Consequently, the cavitation in the TLV core disappears. With decreasing flow rate, this phenomenon becomes more abrupt, occurs further upstream, and the fragments occupy a larger area.

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1997 Best Paper Award—Turbomachinery Committee: A Study of Spike and Modal Stall Phenomena in a Low-Speed Axial Compressor

Cited by 305 publications

References 13 publications

Inception mechanism and suppression of rotating stall in an axial-flow fan

Inception mechanism and suppression of rotating stall in an axial-flow fan

Experimental Investigation of Surge and Stall in a High-Speed Centrifugal Compressor

Visualization and Time-Resolved Particle Image Velocimetry Measurements of the Flow in the Tip Region of a Subsonic Compressor Rotor

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