Separated Flows in Axial Flow Compressor With Variable Stator Vanes at Positive Incidence Angles

Cyrus, V.

doi:10.1115/94-gt-480

Cited by 5 publications

(5 citation statements)

References 10 publications

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“…114 The pressure pulsations arise evidently as a consequence of large region of flow separation on the IGV surface , when vortex systems are formed. A similar phenomenon was observed at the inlet guide vanes of rear stage of axial compressor (Cyrus, 1994).…”

Section: Stage Bladinq With Variable Igv -Case Isupporting

confidence: 73%

“…Large areas of separated flow in the rotor and stator blade rows originated as the diffusion factor D exceeded the critical value D = 0.6 within (1/4 -I13) of the blade height near one end-wall. This conclusion proceeded from the analysis of a larger set of experimental data obtained in a few compressor stages (Cyrus (1986), Cyrus (1994)).…”

Section: D Flow Analysis In Axial-flow Stage Blading the Aerodynamicmentioning

confidence: 99%

“…The above mentioned conclusions are in agreement with the results of measurement of three-dimensional flow in one-stage low-speed stages - Cyrus (1986), McDougall. (1990 and Cyrus (1994), as far as the simultaneous existence of larger areas of stall in rotor and stator row of the stage just before the stability loss is concerned.…”

Section: Nonsteady Flowsmentioning

confidence: 99%

“…The origins of unsteady flows in the stage were also investigated. Some partial results concerning 3D flow through the rear axial compressor stage with variable inlet guide and stator vanes have already been published (Cyrus, 1994).…”

Section: Introductionmentioning

confidence: 99%

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Aerodynamic Performance of an Axial Compressor Stage With Variable Rotor Blades and Variable Inlet Guide Vanes

Cyrus

1998

Volume 1: Turbomachinery

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Experimental investigations of flow fields and losses in an axial flow compressor stage were carried out. The stage has hub/tip ratio of 0.7. The design values of flow coefficient and pressure coefficient are 0.6 and 0.81, respectively. Aerodynamic performance was investigated for two principal configurations: i) axial flow stage with variable rotor blades, ii) axial flow stage with variable inlet guide and stator vanes. The most efficient volume flow rate regulation of the stage was with the application of variable rotor blades. On the basis of experimental data an analysis of the origin of flow separation on the suction and pressure surfaces of rotor and stator blades was made with the use of simple design criteria. The unsteady flow of rotating stall type in the tested stage appeared after simultaneous occurence of large stall regions in both rotor and stator blade rows. The existence of large stall regions in the IGV did not affect the rotating stall onset. At high values of the IGV stagger angle change (50 deg) pressure pulsations appeared due to the occurence of stall.

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Section: Stage Bladinq With Variable Igv -Case Isupporting

confidence: 73%

Section: D Flow Analysis In Axial-flow Stage Blading the Aerodynamicmentioning

confidence: 99%

Section: Nonsteady Flowsmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Aerodynamic Performance of an Axial Compressor Stage With Variable Rotor Blades and Variable Inlet Guide Vanes

Cyrus

1998

Volume 1: Turbomachinery

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“…Some results concerning the mechanism of three-dimensional flow in the blade row of the stage with aspect ratio 1.0 with smooth and distorted inlet velocity profile have been published by Cyrus (1988a).Performance of the rear stage in off-design work regimes are in papers by Cyrus (1990Cyrus ( , 1994.…”

Section: Introductionmentioning

confidence: 99%

Aerodynamic Performance of Rear Axial Compressor Stage With Annular Diffuser and Outlet Chamber

Cyrus

1996

Volume 1: Turbomachinery

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A detailed investigation of aerodynamic performance of three low-speed rear axial compressor stage bladings with the aspect ratios: 0.75, 1.0 and 1.25 was carried out. The bladings of industrial type consist of rotor, stator and outlet guide vanes. The outer and inner diameters of the stage are constant. The hub/tip ratio is 0.871 and the outer diameter is 800 mm. Stage blading is followed by an annular diffuser with outlet chamber. The effect of blade aspect ratio on compressor stage performance was also analysed with the use of straight cascade data. This data supported the test stage experimental results. We found that the effect of aspect ratio on stage performance is not remarkable in the considered range. There are some differences at off-design conditions. The lowest value of blading efficiency was obtained in the case with the lowest aspect ratio value. Three inlet velocity profiles were modelled with the use of lengthened inlet annulus and a screen specially designed. It was found that there is a significant effect of inlet velocity profile distortion on rear compressor stage blading performance for all aspect ratios. Aerodynamic characteristics of compressor stage blading with annular diffuser and outlet chamber were determined. During the investigation we also removed the outlet guide vanes. Therefore the effect of swirl and inlet velocity profile could be investigated.

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Effect of vane opening on aerodynamic performance of the ram-rotor test system

et al. 2016

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In order to research the influence of adjustable vane on the aerodynamic performance of the ram-rotor test system, FLUENT software has been adopted to simulate the flow passage of the ram-rotor test system numerically. The vane opening is controlled by changing the stagger angle of the vane blades. Results show that flow uniformity of vane outlet is influenced by the vane openings, which has an impact on the aerodynamic loss to some extent. Total pressure ratio, adiabatic efficiency and mass flow rate can be regulated by different openings of the vane.Compared with -8° vane opening, top efficiency of the ram-rotor increases by about 13.8% at +6° opening. And total pressure ratio drops by 5.87%. The rising opening increases the relative Mach number at inlet of the ram-rotor and weakens the intensity of the tip clearance leakage, which comes to a decreasing aerodynamic loss.

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Separated Flows in Axial Flow Compressor With Variable Stator Vanes at Positive Incidence Angles

Cited by 5 publications

References 10 publications

Aerodynamic Performance of an Axial Compressor Stage With Variable Rotor Blades and Variable Inlet Guide Vanes

Aerodynamic Performance of an Axial Compressor Stage With Variable Rotor Blades and Variable Inlet Guide Vanes

Aerodynamic Performance of Rear Axial Compressor Stage With Annular Diffuser and Outlet Chamber

Effect of vane opening on aerodynamic performance of the ram-rotor test system

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