The Influence of Tip Clearance Momentum Flux on Stall Inception in a High-Speed Axial Compressor

Cameron, Joshua D.; Bennington, Matthew A.; Ross, Mark; Morris, Scott; Du, Juan; Feng, Lin; Chen, Jingyi

doi:10.1115/1.4007800

Cited by 50 publications

(28 citation statements)

References 34 publications

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“…Vo [2] found that a criterion for spike-type stall inception is that the interface created from the approach flow and the reverse tip-leakage flow becomes parallel with the rotor leading edge plane. Later Cameron et al [3] obtained measurements supporting this concept using the compressor used in the present work. Tan et al [4] provide a comprehensive review on the current understanding of stall inception.…”

Section: Introductionsupporting

confidence: 54%

Observations of the Growth and Decay of Stall Cells during Stall and Surge in an Axial Compressor

Hickman

Morris

2017

International Journal of Rotating Machinery

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This research investigated unsteady events such as stall inception, stall-cell development, and surge. Stall is characterized by a decrease in overall pressure rise and nonaxisymmetric throughflow. Compressor stall can lead to surge which is characterized by quasi-axisymmetric fluctuations in mass flow and pressure. Unsteady measurements of the flow field around the compressor rotor are examined. During the stall inception process, initial disturbances were found within the rotor passage near the tip region. As the stall cell develops, blade lift and pressure ratio decrease within the stall cell and increase ahead of the stall cell. The stall inception event, stall-cell development, and stall recovery event were found to be nearly identical for stable rotating stall and surge cases. As the stall cell grows, the leading edge of the cell will rotate at a higher rate than the trailing edge in the rotor frame. The opposite occurs during stall recovery. The trailing edge of the stall cell will rotate at the approximate speed as the fully developed stall cell, while the leading edge decreases in rotational speed in the rotor frame.

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Section: Introductionsupporting

confidence: 54%

Observations of the Growth and Decay of Stall Cells during Stall and Surge in an Axial Compressor

Hickman

Morris

2017

International Journal of Rotating Machinery

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“…13 Based on this result, it is reasonable to conjecture that circumferential groove casing treatments (CGCT) increase surge margin by altering the axial momentum balance through their interaction with the tip clearance flow field, namely through radial transport of axial momentum. This paper examines this hypothesis through the findings of experiments conducted on a high-speed, single stage axial compressor with several circumferential groove casing treatment geometries as well as information available from simulations of the compressor rotor with a smooth wall.…”

Section: Introductionmentioning

confidence: 92%

Surge Margin Extension and Circumferential Groove Interaction with the Rotor Tip Clearance Flow Field

Ross¹,

Bennington²,

Cameron³

et al. 2014

50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference

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Experimental and computational studies were conducted to study the role of the tip leakage flow in axial compressor stall and the relationship between the tip clearance flow field and surge margin extension from circumferential groove casing treatment (CGCT). Experimental measurements of surge margin extension from seven CGCT configurations with a fixed groove geometry demonstrated that the contribution of individual grooves in a multi-groove casing to surge margin extension is an (a) additive and (b) linear function of the smooth wall tip clearance axial momentum flux at the location of a each groove. Cameron et al.'s 2013 axial momentum model of the rotor tip clearance was extended to include the influence of a CGCT. Control volume analysis of this model showed that circumferential grooves reduce the tip leakage flow axial momentum through radial transport. The equivalent force due to a circumferential groove was demonstrated to be related to the smooth wall tip clearance axial momentum flux through a coefficient of drag that had a log-linear dependence on groove aspect ratio. The paper closes with a demonstration of how findings from the experiments described above can combine with the one-dimensional momentum balance to make first-order estimates of surge margin extension from a given circumferential groove casing treatment.

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“…As for the rotor limiting streamlines, it is observed that the vortex flow region of RANS solution dominates in hub region. However, the vortical flow motions occur (6) where Ω is vorticity magnitude, S is mean strain rate. It is found that the two vortex structures predicted by RANS and DES are clearly different from each other as seen in Figs.…”

Section: (5)mentioning

confidence: 99%

“…They discovered that the cyclical motion of tip secondary vortex was the main source of the nearly periodic variation of efficiency. Cameron et al [6] studied the role of tip leakage flow in axial compressor stall by the experiments and computations. The results confirmed that the compressor stalled when an interface between the approach flow and the tip-leakage flow reached the rotor leading edge plane as flow coefficient was reduced.…”

Section: Introductionmentioning

confidence: 99%

A Comparative Study of Numerical Methods on Aerodynamic Characteristics of a Compressor Rotor at Near-stall Condition

Kim¹,

Kim²,

Choi³

et al. 2015

International Journal of Aeronautical and Space Sciences

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The present work performs three-dimensional flow calculations based on Reynolds Averaged Navier-Stokes (RANS) and Delayed Detached Eddy Simulation (DDES) to investigate the flow field of a transonic rotor (NASA Rotor 37) at near-stall condition. It is found that the DES approach is likely to predict well the complex flow characteristics such as secondary vortex or turbulent flow phenomenon than RANS approach, which is useful to describe the flow mechanism of a transonic compressor. Especially, the DES results show improvement of predicting the flow field in the wake region and the model captures reasonably well separated regions compared to the RANS model. Besides, it is discovered that the three-dimensional vortical flows after the vortex breakdown from the rotor tip region are widely distributed and its vortex structures are clearly present. Near the rotor leading edge, a part of the tip leakage flows in DES solution spill over into next passage of the blade owing to the separation vortex flow and the backflow is clearly seen around the trailing edge of rotor tip. Furthermore, the DES solution shows strong turbulent eddies especially in the rotor hub, rotor tip section and the downstream of rotor trailing edge compared to the RANS solution.

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The Influence of Tip Clearance Momentum Flux on Stall Inception in a High-Speed Axial Compressor

Cited by 50 publications

References 34 publications

Observations of the Growth and Decay of Stall Cells during Stall and Surge in an Axial Compressor

Observations of the Growth and Decay of Stall Cells during Stall and Surge in an Axial Compressor

Surge Margin Extension and Circumferential Groove Interaction with the Rotor Tip Clearance Flow Field

A Comparative Study of Numerical Methods on Aerodynamic Characteristics of a Compressor Rotor at Near-stall Condition

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