An Experimental and Computational Investigation of Tip Clearance Flow and Its Impact on Stall Inception

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

doi:10.1115/gt2010-23516

Cited by 20 publications

(13 citation statements)

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“…Since such an MF/TLF interface exists in the rotor's rotating reference frame, how it looks like on the casing stationary reference frame becomes crucial to experimentists. Cameron et al [14] demonstrated that on casing the complex 3D curvy oscillatory surface of MF/TLF in the rotor rotating frame can be observed as a straight line on the casing stationary frame, as seen in Figure 9 [14]. This is because, when observed at casing, the spatial and temporal variations within the rotor frame are all naturally averaged.…”

Section: The Role Of Axial Momentum and The (Bell-shaped) Curvementioning

confidence: 99%

Oscillatory Tip Leakage Flows and Stability Enhancement in Axial Compressors

Feng

Chen

2018

International Journal of Rotating Machinery

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Rotating stall axial compressor is a difficult research field full of controversy. Over the recent decades, the unsteady tip leakage flows had been discovered and confirmed by several research groups independently. This paper summarizes the research experience on unsteady tip leakage flows and stability enhancement in axial flow compressors. The goal is to provide theoretical bases to design casing treatments and tip air injection for stall margin extension of axial compressor. The research efforts cover (1) the tip flow structure at near stall that can explain why the tip leakage flows go unsteady and (2) the computational and experimental evidences that demonstrate the axial momentum playing an important role in unsteady tip leakage flow. It was found that one of the necessary conditions for tip leakage flow to become unsteady is that a portion of the leakage flow impinges onto the pressure side of the neighboring blade near the leading edge. The impediment of the tip leakage flow against the main incoming flow can be measured by the axial momentum balance within the tip range. With the help of the theoretical progress, the applications are extended to various casing treatments and tip air recirculation.

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Section: The Role Of Axial Momentum and The (Bell-shaped) Curvementioning

confidence: 99%

Oscillatory Tip Leakage Flows and Stability Enhancement in Axial Compressors

Feng

Chen

2018

International Journal of Rotating Machinery

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“…Another condition required for spike inception is that the flow from tip-clearance region of one blade moves across the blade passage of the adjacent one by passing around T.E. This gives origin to a backflow that impinges on the pressure side and increases its pressure, thus generating a higher blockage (Vo [2], 2005, Bennington et al [4], 2010 and Deppe et al [5], 2005). A sketch that explains the basic flow features related to this criterion is shown in Figure 1 (left).…”

Section: Forward Spillage Mechanismmentioning

confidence: 99%

“…A conceptual framework that could be exploited to derive useful design considerations when tip clearance is present, is discussed in Bennington et al [4] (2010). According to their work, the interface between the main flow and the tip leakage flow can be effectively defined by the locus where the axial velocity reverses its sign.…”

Section: Design Variables Affecting the Spike-stallmentioning

confidence: 99%

Rotor tip stall from a designer's perspective

Schneider

Silingardi

Astrua

et al. 2017

European Conference on Turbomachinery Fluid Dynamics and Hermodynamics

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The operating range of a compressor is the most critical aspect to consider when dealing with new designs. Two distinct routes to compressor stall are known in literature: modal-stall that occurs near the peak of the overall characteristic and spike-stall that initiates on the negatively-sloped part of the characteristic curve. Modal type stall can be taken into account from the very beginning during the design process. The basic mechanisms that drive the phenomena are essentially 2D in nature and there are well-established and experimentally validated design criteria available. Unfortunately this statement no longer applies when dealing with spike-type stall. This short length-scale instability is related to a threedimensional breakdown of the flow that appears at rotor tip. Since when firstly observed, much effort has been expended trying to understand the flow features underlying this abrupt stall. Nevertheless, a well-established and validated design criterion is still missing. This paper deals with the topic from a designer's perspective. A discussion which tries to highlight the design variables affecting the spike-stall is presented in the first part of the paper. Then CFD results on core stages of an heavy-duty axial compressor are discussed. The aim is to derive useful considerations for the designer work and discuss which design actions are more effective to successfully complete a spike-stall safe design.

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“…They found the disturbance grew as the tip clearance narrowed to its minimum and decayed as the tip clearance expanded to its maximum at the stall inception. Using the same facility as Cameron et al, Bennington et al (2010) calculated the location in which momentums of incoming passage flow and tip-leakage flow were balanced. They argued that compressor exhibits rotating stall when this momentum balance breaks down at the rotor leading edge with the largest tip clearance.…”

Section: Introductionmentioning

confidence: 99%

Measurement of Shrouded Radial Compressor Stability under Eccentric Conditions

Kim¹,

Song²,

Park³

et al. 2019

GPPS Zurich19

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This paper reports on the measurement of the impact of impeller eccentricity on the stability of a radial compressor. The test radial compressor is a shrouded type with a vaneless diffuser. The relative eccentricity between the impeller and the casing has been achieved by offsetting the casing with precision shims. The eccentric impeller induces tangential flow redistribution, resulting in non-axisymmetric flow field, especially at the impeller exit. At the design condition, eccentricity has little influence on the compressor pressure rise. However, near the instability onset point, pressure rise decreases slightly as the eccentricity is increased. Under the baseline conditions, the compressor goes directly into classic surge at the flow coefficient of 0.0218. However, under eccentric conditions, the compressor goes into rotating stall first and then goes into surge. Before going into rotating stall, the compressor exhibits a modal-type stall behavior. With increasing eccentricity, rotating stall onset flow coefficient increases, but the subsequent surge appears at the same flow coefficient of 0.0218.

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An Experimental and Computational Investigation of Tip Clearance Flow and Its Impact on Stall Inception

Cited by 20 publications

References 0 publications

Oscillatory Tip Leakage Flows and Stability Enhancement in Axial Compressors

Oscillatory Tip Leakage Flows and Stability Enhancement in Axial Compressors

Rotor tip stall from a designer's perspective

Measurement of Shrouded Radial Compressor Stability under Eccentric Conditions

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