Rotating Stall Control in a High-Speed Stage With Inlet Distortion: Part I—Radial Distortion

Spakovszky, Z. S.; Weigl, Harald J.; Paduano, James D.; Schalkwyk, C. M. van; Suder, Kenneth L.; Bright, Michelle M.

doi:10.1115/1.2841345

Cited by 100 publications

(24 citation statements)

References 12 publications

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“…These latter results are consistent with those obtained by Hoying et al (1999). It has been recognized that the radial distribution of the axial velocity along the blade span is an important parameter for the stall inception mode in axial compressors (Spakovszky et al, 1999). To find out the propagation characteristics of the stall cells in the radial and circumferential directions, the contours of negative axial velocities at a 50% axial chord cross plane are shown in Fig.…”

Section: Referring Tosupporting

confidence: 88%

Multiple spike stall cells in low speed axial compressor rotor blade row

Taghavi-Zenouz¹,

Abbasi²

2015

jtam

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Inception and development of multiple stall cells of short length scales are numerically investigated in an axial compressor rotor blade row. The method of investigation is based on time accurate three-dimensional full annulus simulations. Time dependent flow structure results revealed that there are two criteria responsible for inception of a special kind of stall, introduced as spike stall in the literature. These criteria are defined as leading edge spillage and trailing edge backflow, which occur at specific mass flow rates near to stall conditions. The numerical results revealed that once the spike stall cells appear, they cover roughly two blade passages in the circumferential direction and cover about 25% of the blade height. By further revolution of the blade row, the number of cells tends to increase. For the present case study, the number of stall cells increased to three after 8.5 rotor revolutions from the moment of the initial spike stall occurrence. Even at this moment, both of the above mentioned criteria for the spike stall inception have been observed within the blades passages. These events caused the inlet relative flow angle to the blade rows, and therefore the flow incidence angle and consequent blockage to the main flow, to increase. The tip leakage flow frequency spectrum has been studied through surveying instantaneous static pressure signals imposed on pressure side of the blades and also on the casing walls. These latter results showed that any further revolving of the rotor blade row, exceeding 8.5 revolutions, causes the spike stall to disturb the flow structure significantly.

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Section: Referring Tosupporting

confidence: 88%

Multiple spike stall cells in low speed axial compressor rotor blade row

Taghavi-Zenouz¹,

Abbasi²

2015

jtam

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“…Both experimental (Spakovszky et al, 1999 andSuder et al 2001) and computational studies (Chen et al, 2006, Davis andYao et al, 2006) indicate the rotating stall of this compressor initiates in the rotor tip region, so the analysis will focus on the rotor tip. Instantaneous pressure profiles around the annulus near the rotor tip leading edge are shown in figure 11.…”

Section: Development Of Long-length Disturbancementioning

confidence: 99%

Prestall Behavior of a Transonic Axial Compressor Stage via Time-Accurate Numerical Simulation

Chen¹,

Hathaway²,

Herrick³

2008

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CFD calculations using high-performance parallel computing were conducted to simulate the pre-stall flow of a transonic compressor stage, NASA compressor Stage 35. The simulations were run with a full-annulus grid that models the 3D, viscous, unsteady blade row interaction without the need for an artificial inlet distortion to induce stall. The simulation demonstrates the development of the rotating stall from the growth of instabilities. Pressure-rise performance and pressure traces are compared with published experimental data before the study of flow evolution prior to the rotating stall. Spatial FFT analysis of the flow indicates a rotating long-length disturbance of one rotor circumference, which is followed by a spike-type breakdown. The analysis also links the long-length wave disturbance with the initiation of the spike inception. The spike instabilities occur when the trajectory of the tip clearance flow becomes perpendicular to the axial direction. When approaching stall, the passage shock changes from a single oblique shock to a dual-shock, which distorts the perpendicular trajectory of the tip clearance vortex but shows no evidence of flow separation that may contribute to stall. REPORT DOCUMENTATION PAGE Form ApprovedThis publication is available from the NASA Center for AeroSpace Information, 301-621-0390 SUPPLEMENTARY NOTES ABSTRACTCFD calculations using high-performance parallel computing were conducted to simulate the pre-stall flow of a transonic compressor stage, NASA compressor Stage 35. The simulations were run with a full-annulus grid that models the 3D, viscous, unsteady blade row interaction without the need for an artificial inlet distortion to induce stall. The simulation demonstrates the development of the rotating stall from the growth of instabilities. Pressure-rise performance and pressure traces are compared with published experimental data before the study of flow evolution prior to the rotating stall. Spatial FFT analysis of the flow indicates a rotating long-length disturbance of one rotor circumference, which is followed by a spike-type breakdown. The analysis also links the long-length wave disturbance with the initiation of the spike inception. The spike instabilities occur when the trajectory of the tip clearance flow becomes perpendicular to the axial direction. When approaching stall, the passage shock changes from a single oblique shock to a dual-shock, which distorts the perpendicular trajectory of the tip clearance vortex but shows no evidence of flow separation that may contribute to stall. SUBJECT TERMSTransonic compressor; Rotating stall; Simulations 16. SECURITY CLASSIFICATION OF: 17. LIMITATION OF ABSTRACT UU 18. NUMBER OF PAGES 20 19a. NAME OF RESPONSIBLE PERSON STI Help Desk (email:help@sti.nasa.gov) a. REPORT U b. ABSTRACT U c. THIS PAGE U 19b. TELEPHONE NUMBER (include area code) 301-621-0390 Standard Form 298 (Rev. 8-98) Prescribed by ANSI Std. Z39-18

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“…Spakovszky et al [23], Koch and Smith [24], Lee and Greitzer [25], and Suder et al [26] studied the effect of tip injection on the compressor stability. Another common control strategy, air bleeding, utilizes some bleed valves around the compressor casing.…”

Section: Introductionmentioning

confidence: 99%

Stall inception in a transonic axial fan

Khaleghi

Boroomand

Tousi

et al. 2008

Proceedings of the Institution of Mechanical Engineers, Part A:

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The current paper reports a numerical investigation of stall inception in a transonic compressor rotor, NASA Rotor-67, by using the whole flow passages in the computations. Surface roughness is added to one of the blades in order to trigger rotating stall. During stall inception, the tip clearance vortex moved away from the suction surface of the roughened blade's upper neighbour, leading to vortex breakdown. The stall cell was found to propagate opposite the direction of the blade rotation at about 30 per cent of rotational speed. The effect of air bleeding on stabilizing the compressor is also studied in this work. The mean mass flowrate removed from the bleed valves was 1.2 per cent of the mainstream flowrate. This amount of bleeding was found to effectively suppress the stalling disturbances.

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Rotating Stall Control in a High-Speed Stage With Inlet Distortion: Part I—Radial Distortion

Cited by 100 publications

References 12 publications

Multiple spike stall cells in low speed axial compressor rotor blade row

Multiple spike stall cells in low speed axial compressor rotor blade row

Prestall Behavior of a Transonic Axial Compressor Stage via Time-Accurate Numerical Simulation

Stall inception in a transonic axial fan

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