An experimental description of the flow in a centrifugal compressor from alternate stall to surge

Moënne-Loccoz, V.; Trébinjac, Isabelle; Bénichou, Emmanuel; Goguey, S.; Paoletti, Benoît; Laucher, Pierre

doi:10.1007/s11630-017-0941-8

Cited by 12 publications

(3 citation statements)

References 8 publications

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“…This performance map is also divided into 3 areas colored in white, blue and pink in Figure 2. Indeed, previous work [12][13][14] on the compressor has shown the possible setting of an alternate stall pattern over two adjacent channels in the radial diffuser at partial rotation speed. In such an alternate pattern, one diffuser passage is stalled, the adjacent passage is free and this pattern is repeated all around the circumference.…”

Section: Path To Surgementioning

confidence: 99%

Low frequency stall modes of a radial vaned diffuser flow

Moënne-Loccoz

Trébinjac

Poujol

et al. 2019

Mechanics & Industry

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The present paper aims at providing an experimental analysis of the path to surge of a centrifugal compressor stage designed and built by Safran Helicopter Engines. Depending on the rotation speed of the compressor, two distinct flow patterns are observed in the radial diffuser at stabilized operating points near the surge, an asymmetric and a symmetric pattern. At medium rotation speed, the alternate pattern consisting of a two-channel pattern in the radial diffuser develops. One passage over two is stalled, the adjacent passage is free and this pattern replicates over the whole circumference while pulsing at a frequency of roughly 12 Hz which is close to the Helmholtz frequency of the test rig. By lowering the rotation speed, the two-channel pattern fades away and gives way to a periodical behavior of the radial diffuser passages called symmetric mode. The flow in each channel is identical presenting a stalled behavior pulsating in phase at a higher frequency of roughly 42 Hz. The two 12 Hz and 42 Hz modes are described and their existences are imputed to a lock-in of the natural frequencies of the instabilities with the acoustic modes of the test rig.

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Section: Path To Surgementioning

confidence: 99%

Low frequency stall modes of a radial vaned diffuser flow

Moënne-Loccoz

Trébinjac

Poujol

et al. 2019

Mechanics & Industry

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“…Rotating disturbances have been observed at the low rotation speed L2 on a large mass flow range at the stagger angle TURBO-21-1015, POUJOL 0° during previous work [15]. These rotating disturbances are in fact rotating instabilities according to the description of rotating instabilities proposed by Day [1].…”

Section: Delay Of the Onset Of Rotating Instabilities At Low Rotation Speedsmentioning

confidence: 78%

“…Previous work on the compressor at an IGV stagger angle of 0° has been carried out by Moënne-Loccoz et al [13,15]. Rotating instabilities at the impeller inlet have been observed, the impact of the IGV stagger angle on the development of these rotating instabilities is discussed in the last part.…”

Section: Performance Map and Variation Of The Choked Mass Flow Ratementioning

confidence: 95%

Effects of Inlet Guide Vanes on the Performance and Stability of an Aeronautical Centrifugal Compressor

Poujol

Trébinjac

Duquesne

2021

Journal of Turbomachinery

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A research centrifugal compressor stage designed and built by Safran Helicopter Engines is tested at 3 IGV (Inlet Guide Vanes) stagger angles. The methodology for calculating the performance is detailed, including the consideration of humidity in order to minimize errors related in particular to operating atmospheric conditions. The shift of the surge line towards lower mass flow rate as the IGV stagger angle increases highly depends on the rotation speed. The surge line shift is very small at low rotation speeds whereas it significantly increases at high rotation speeds. A first-order stability analysis of the impeller and diffuser sub-components shows that the diffuser (resp. impeller) is the first unstable component at low (resp. high) rotation speeds. This situation is unaltered by increasing the IGV stagger angle. At low rotation speeds below a given mass flow rate, rotating instabilities at the impeller inlet are detected at zero IGV stagger angle. Their occurrence is conditioned by the relative flow angle at the tip of the leading edge of the impeller. As the IGV stagger angle increases, the mass flow decreases to maintain a given inlet flow angle. Therefore, the onset of the rotating instabilities is delayed towards lower mass flow rates. At high rotation speeds, the absolute flow angle at the diffuser inlet near surge decreases as the IGV stagger angle increases. As a result, the flow is highly alternate over two adjacent channels of the radial diffuser beyond the surge line at IGV stagger angle of 0°.

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Experimental Study on Inducement and Development of Flow Instabilities in a Centrifugal Compressor with Different Diffuser Types

Xue

Wang

2020

J. Therm. Sci.

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An experimental description of the flow in a centrifugal compressor from alternate stall to surge

Cited by 12 publications

References 8 publications

Low frequency stall modes of a radial vaned diffuser flow

Low frequency stall modes of a radial vaned diffuser flow

Effects of Inlet Guide Vanes on the Performance and Stability of an Aeronautical Centrifugal Compressor

Experimental Study on Inducement and Development of Flow Instabilities in a Centrifugal Compressor with Different Diffuser Types

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