Numerical analysis of the tip leakage flow field in a transonic axial compressor with circumferential casing treatment

Legras, Guillaume; Gourdain, Nicolas; Trébinjac, Isabelle

doi:10.1007/s11630-010-0198-y

Cited by 15 publications

(11 citation statements)

References 10 publications

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“…The characteristics of rotating stall in a centrifugal compressor impeller will be compared between the numerical results produced by a commercial solver to a set of experimental results for the same compressor. 24 Axial compressor Rotor blade tip In-house code (MIT) März et al 25 Axial compressor Rotor blade tip In-house code (NASA) Chen et al 23 Axial compressor Rotor blade tip In-house code (OSU) Legras et al 26 Axial compressor Rotor blade tip elsA ONERA Choi et al 27 Axial fan Rotor In-house code (Rolls-Royce) Sano et al 28 Centrifugal pump Vaned diffuser SCRYU/Tetra Lucius and Brenner 29 Centrifugal pump Rotor ANSYS CFX Table 2. Documented cases of rotating stall in numerical simulations for centrifugal compressors.…”

Section: Introductionmentioning

confidence: 99%

Prediction of impeller rotating stall onset using numerical simulations of a centrifugal compressor. Part 1: Detection of rotating stall using fixed-flow transient simulations

Vagani

Engeda

Cave³

2013

Proceedings of the Institution of Mechanical Engineers, Part A:

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Rotating stall is an unsteady flow phenomenon that appears in both axial and centrifugal compressors. It is detrimental to the performance of the compressor, significantly narrowing its operating range. Numerical modeling of this phenomenon has been a major area of investigation for axial compressors with some success. While stall occurs less often in centrifugal compressors than axial ones, it can be much harder to predict. Some preventive measures are known but are mostly rules of thumb developed through experimental experience. This work focuses on the detection of impeller rotating stall using computational fluid dynamics. A compressor was chosen that has demonstrated rotating stall instabilities with different diffuser lengths and return vanes. Unsteady numerical simulations were performed on full 360 models of this geometry. The transient simulations were conducted using distributed processing on high-performance servers. The objective was to determine the accuracy in which rotating stall can be captured in simulations. For this purpose, simulation results were compared to experimental results for the same compressor and show a good correlation between the experimental and numerical tests.

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Section: Introductionmentioning

confidence: 99%

Prediction of impeller rotating stall onset using numerical simulations of a centrifugal compressor. Part 1: Detection of rotating stall using fixed-flow transient simulations

Vagani

Engeda

Cave³

2013

Proceedings of the Institution of Mechanical Engineers, Part A:

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“…The implementation of casing grooves is only investigated through numerical simulations. The CT geometry is taken from Legras et al [8] and consists of 6 circumferential slots ( Figure 5(a)). Each groove is 3 mm wide (10.9% of rotor tip axial chord) with a gap of 1.5 mm between each cavity.…”

Section: Description Of the Investigated Axial Compressorsmentioning

confidence: 99%

“…Thus stall prevention techniques must be used, and one promising technology known to bring substantial stability for tip critical compressor rotor is casing treatment (CT) [1]. This passive control device consists of slots within the rotor casing and presents various types of geometries: circumferential grooves [2][3][4][5][6][7][8][9], nonaxisymmetric slot-type CT [10][11][12][13][14] and self-recirculating flow channels [15][16][17], and honeycomb [18]. Hathaway [19] provides an extensive overview of the research studies over the last 50 years that attempt to uncover the physics behind the improvement in stall margin.…”

Section: Introductionmentioning

confidence: 99%

A Novel Approach to Evaluate the Benefits of Casing Treatment in Axial Compressors

Legras

Trébinjac

Gourdain

et al. 2012

International Journal of Rotating Machinery

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Passive control devices based on casing treatments have already shown their capability to improve the flow stability in axial compressors. However, their optimization remains complex due to a partial understanding of the related physical mechanisms. In order to quantitatively assess the interaction between slots and the blade tip flow, the present paper develops a novel analysis methodology based on a control-volume approach located in the rotor tip region. This methodology may be used for analyzing the casing treatment based on both axi-and non-axisymmetric slots design. The second issue of the paper focuses on the application of the current approach to better understand the effects of axi-and non-axisymmetric grooves in three different axial compressors which differ by the flow regime (subsonic/transonic) and the smooth casing shape (cylindrical/concave). Numerical simulations are performed, and results of the current approach with and without casing treatments are compared.

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“…showed that the spike instabilities occur when the trajectory of the tip clearance flow becomes perpendicular to the axial direction. Legras et al (2010) studied on the effect of circumferential grooves on the tip leakage flow and its resulting vortical flow structures. They observed that the grooves could change the trajectory of tip leakage vortex and in addition generate a set of secondary tip leakage vortices.…”

Section: Introductionmentioning

confidence: 99%

Numerical Study on the Effect of Single Shallow Circumferential Groove Casing Treatment on the Flow Field and the Stability of a Transonic Compressor

Mirzabozorg

Bazazzadeh

Hamzezade

2017

JAFM

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The present research investigates the effect of the location and the width of single shallow circumferential groove casing treatment on the flow field and the stability improvement of NASA Rotor 37 utilizing the help of computational fluid dynamics. At first, steady state simulation of Rotor37 was presented for smooth casing (without groove). Then, forty five various grooved casing were simulated and compared with the smooth casing. The results indicated that narrow grooves had slight effect on the adiabatic efficiency but as the width of the groove was increased, a decline in efficiency was observed. The investigation on the stall margin revealed that narrow grooves next to the leading edge could improve the stall margin by a reduction in the size of vortex breakdown zone. Medium-width grooves displayed an effective role in delaying the separation-produced by shock wave and boundary layer interaction-on the blade suction side near the casing. This type of grooves could improve the stall margin more than narrow grooves when located on the top of separation zone near the blade suction side. Wide grooves had negative effect on the stall margin and caused a significant drop in the efficiency and the total pressure ratio of the compressor.

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Numerical analysis of the tip leakage flow field in a transonic axial compressor with circumferential casing treatment

Abstract: International audienc

Cited by 15 publications

References 10 publications

Prediction of impeller rotating stall onset using numerical simulations of a centrifugal compressor. Part 1: Detection of rotating stall using fixed-flow transient simulations

Prediction of impeller rotating stall onset using numerical simulations of a centrifugal compressor. Part 1: Detection of rotating stall using fixed-flow transient simulations

A Novel Approach to Evaluate the Benefits of Casing Treatment in Axial Compressors

Numerical Study on the Effect of Single Shallow Circumferential Groove Casing Treatment on the Flow Field and the Stability of a Transonic Compressor

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