Investigation of Pre-Stall Mode and Pip Inception in High Speed Compressors Through the Use of Correlation Integral

Bright, Michelle M.; Qammar, Helen; Wang, Leizhen

doi:10.1115/98-gt-365

Cited by 3 publications

(2 citation statements)

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“…Time-resolved pressure measurement of Stage 35 near stall was reported by Bright et al (1999). The experiment was performed at 85% design speed.…”

Section: Relevant Experimental Workmentioning

confidence: 99%

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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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“…Time-resolved pressure measurement of Stage 35 near stall was reported by Bright et al (1999). The experiment was performed at 85% design speed.…”

Section: Relevant Experimental Workmentioning

confidence: 99%

“…-Experiment pressure traces for clean inlet, 85% design speed, Stage 35, MichelleBright et al (1999).…”

mentioning

confidence: 99%

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

Chen¹,

Hathaway²,

Herrick³

2008

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Effect of Rotating Inlet Distortion with Multi-distorted Regions on Compressor Stability

Wang,

Fan,

et al. 2024

Int. J. Aeronaut. Space Sci.

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A Stall Warning Scheme for Aircraft Engines With Inlet Distortion via Deterministic Learning

Lin

Chen

2018

IEEE Trans. Contr. Syst. Technol.

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Investigation of Pre-Stall Mode and Pip Inception in High Speed Compressors Through the Use of Correlation Integral

Cited by 3 publications

References 4 publications

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

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

Effect of Rotating Inlet Distortion with Multi-distorted Regions on Compressor Stability

A Stall Warning Scheme for Aircraft Engines With Inlet Distortion via Deterministic Learning

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