A Correlation for Tip Leakage Blockage in Compressor Blade Passages

Hoeger, Martin; Lahmer, M.; Dupslaff, M.; Fritsch, G.

doi:10.1115/1.1303707

Cited by 15 publications

(5 citation statements)

References 13 publications

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“…It is of course to keep in mind that stall onset in transonic compressors is in many cases due to flow features linked to the clearance vortex at the blade tip (Vo [7]). In subsonic compressors the tip clearance vortex generates a region of very low axial velocity, also known as blockage (Storer [8,9], Hoeger [10,11], Khalid [12]). However, compared to subsonic cases there is a significant stronger vortex in supersonic ones.…”

Section: Nomenclature Mmentioning

confidence: 99%

Shape of Characteristics of a Transonic Compressor

Pixberg¹,

Mûller²,

Leichtfuß³

et al. 2012

48th AIAA/ASME/SAE/ASEE Joint Propulsion Conference &Amp;amp; Exhibit

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In this paper results from a transonic single-stage axial compressor test facility are presented and discussed concerning the shape of characteristics. For this purpose data of two similar configurations with and without casing treatments are tested. Observing the various characteristics one significant aspect appears: For nearly the whole working range (despite choke) the curve is unexpectedly flat and in several cases the curve even starts rolling (turning) over. This effect is more relevant in the transonic cases but also present for subsonic rotational speeds. However, the compressor is operating in stable mode until at stalling mass flow transient pressure traces reveal instabilities. From the same measurements clear spike-type stall indications are detectable, being distinctive for tip-critical rotors, where flow features at the tip are responsible for stall. For further investigation the data of the stage performance measurements are analyzed for different radial blade height positions in more detail. Apparently, the roll-over of the characteristics results from the upper mid-span region and not, as expected, directly from tip or hub. The reason for this is seen in an exaggerated increase of blockage spreading out from tip towards the upper mid-span while throttling the compressor. On one side this causes a region of comparatively high total temperature ratios but more significantly this region is characterized by high losses mainly due to mixing effects. By this, the efficiency values in the upper mid-span formerly intended by design are decreased over proportionally. By probe measurements and numerical results it could be affirmed that it is not primarily about stator flow phenomena but the effect is already apparent at the rotor exit plane and directly linked to the tip leakage vortex. Finally, the results are discussed in terms of a stall type model detecting the type depending on the curve gradient at stall onset.

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Section: Nomenclature Mmentioning

confidence: 99%

Shape of Characteristics of a Transonic Compressor

Pixberg¹,

Mûller²,

Leichtfuß³

et al. 2012

48th AIAA/ASME/SAE/ASEE Joint Propulsion Conference &Amp;amp; Exhibit

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“…Techniques such as blade tip reshaping, magazine treatment, suction, blowing treatment, plasma discharge, and blade tip winglet technology are prevalently implemented as active and passive measures for controlling blade tip leakage flow.Numerous studies have been carried out by many scholars for the blade tip leakage flow control methods and aerodynamic noise reduction.A.For instance, Maaloum et al [ 1 ] found the important noise sources corresponding to the high pressure fluctuation region located at the blade tip using potential flow methods; Jung,J.H [ 2 ] analyzed the flow structure at the blade tip due to the position of the winglets and confirmed the existence of an optimal blade tip clearance. Hoeger [ 3 ] pointed out the existence of peak blockages in the channel based on numerical simulation results of a large number of transonic compressor rotors and blade grilles,whose distribution characteristics were clearly influenced by the interaction of leakage vortices and excitation waves. Liu B [ 4 ] quantitatively analyzed the characteristics of the blockage distribution in the rotor channel under different measurement conditions, and the blade tip leakage blockage showed nonlinear and nonmonotonic characteristics.…”

Section: Introductionmentioning

confidence: 99%

Effect of tip winglet position on tip flow and noise of axial flow fan

Li¹,

Ge²,

Liu³

et al. 2023

Heliyon

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“…4–6 Meanwhile, many empirical models have been proposed to estimate the tip blockage, loss production, or vortex trajectory caused by TLF in the tip region. 7–10 The influence of tip clearance size (TCS) on the flow structure of TLF is also a focus of many research efforts. It is found that the onset point of TLV is usually at the maximum loading of the blade and a higher TCS moves the position of the highest loading further downstream thus delaying the roll up of the TLV.…”

Section: Introductionmentioning

confidence: 99%

Effect of casing aspiration on the tip leakage flow in the axial flow compressor cascade

Mao

Liu

Tang

2017

Proceedings of the Institution of Mechanical Engineers, Part A:

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Tip leakage flow is usually responsible for the deterioration of compressor performance and stability. The current paper conducts numerical simulations on the impact of casing aspiration on the axial compressor cascade performance. Three aspiration schemes with different chordwise coverage are studied and analyzed. It is found that the cascade performance can be effectively improved by the appropriate casing aspiration, and the optimum aspiration scheme should cover the area including the onset point of tip leakage vortex and its vicinity. The control mechanisms are different for the aspiration schemes located at different blade chord ranges. For the aspiration scheme covering the onset point of tip leakage vortex, the improvement of the cascade performance is mainly due to that the starting point of the tip leakage vortex is shifted downstream. The original tip leakage vortex structure is divided into two parts if the aspiration scheme is located behind the onset point of tip leakage vortex and the final control effect is the combination of the influence from the two different parts of tip leakage vortex. Additionally, the casing aspiration redistributes the blade loading along the chord near blade tip. The results of these investigations may offer guidance for the appropriate design of aspiration scheme in the future updated compressors and the overall total pressure loss coefficient caused by aspiration slot should be considered in the design process.

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A Correlation for Tip Leakage Blockage in Compressor Blade Passages

Cited by 15 publications

References 13 publications

Shape of Characteristics of a Transonic Compressor

Shape of Characteristics of a Transonic Compressor

Effect of tip winglet position on tip flow and noise of axial flow fan

Effect of casing aspiration on the tip leakage flow in the axial flow compressor cascade

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