Delay of Rotating Stall in Compressors Using Plasma Actuators

Ashrafi, Farzad; Michaud, Mathias; Vo, Huu Duc

doi:10.1115/1.4032840

Cited by 24 publications

(12 citation statements)

References 31 publications

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“…Shrouds and winglets, however, must be cooled and add extra weight, which is not desirable. Other conceivable methods of flow control include the use of plasma actuators (e.g., see Saddoughi et al [7] and Ashrafi et al [8]) and blowing from the tip or casing.…”

Section: Introductionmentioning

confidence: 99%

Control of Tip Leakage in a High-Pressure Turbine Cascade Using Tip Blowing

Volino

2017

Journal of Turbomachinery

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Blowing from the tip of a turbine blade was studied experimentally to determine if total pressure loss could be reduced. Experiments were done with a linear cascade in a low-speed wind tunnel. Total pressure drop through the blade row and secondary velocity fields in the passage between two blades were measured. Cases were documented with various blowing hole configurations on flat and squealer tipped blades. Blowing normal to the tip was not helpful and in some cases increased losses. Blowing from the bottom of a squealer cavity provided little benefit. With a flat tip, blowing from holes located near and inclined toward the pressure side generally reduced total pressure drop by reducing the effect of the tip leakage vortex. Holes near the axial location of maximum loading were most helpful, while holes closer to the leading and trailing edges were not as effective. Higher jet velocity resulted in larger total pressure drop reduction. With a tip gap of 1.5% of axial chord, jets with a velocity 1.5 times the cascade inlet velocity had a significant effect. A total pressure drop reduction of the order 20% was possible using a jet mass flow of about 0.4% of the main flow. Jets were most effective with smaller tip gaps, as they were more able to counter the leakage flow.

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Section: Introductionmentioning

confidence: 99%

Control of Tip Leakage in a High-Pressure Turbine Cascade Using Tip Blowing

Volino

2017

Journal of Turbomachinery

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“…One approach is using active flow control techniques such as using plasma actuators. Saddoughi et al 17 studied the tip clearance flow in a transonic compressor with and without plasma actuators and Ashrafi et al 18 investigated the effect of the actuator plasma on the delaying the rotating stall in compressors. Blowing air from the tip or casing wall is another type of active control techniques that can be applied to reduce the tip leakage flows.…”

Section: Introductionmentioning

confidence: 99%

Effect of in-service burnout effect on the transonic leakage flows over cavity tip model

Saleh

Avital

Korakianitis

2021

Proceedings of the Institution of Mechanical Engineers, Part A:

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Increasing the gas temperature at the inlet to the high pressure turbine of gas turbine engines is known as a proven method to increase the efficiency of these engines. However, this will expose the blades’ surface to very high heat load and thermal damages. In the case of the un-shrouded turbine blades, the blade tip will be exposed to a significant thermal load due to the developed leakage flows in the tip gap, this leads to in-service burnout which degrades the blade tip and shortens its operational life. This paper studies the in-service burnout effect of the transonic tip flows over a cavity tip which is a configuration commonly used to reduce the tip leakage flows. This investigation is carried out experimentally within a transonic wind tunnel and computationally using steady and unsteady Reynolds Averaged Navier Stokes approaches. Various flow measurements are established and different flow behaviour including separation bubbles, shockwave development and distinct flow interactions are captured and discussed. It is found that when the tip is exposed to the in-service burnout, leakage flow behaves in a significantly different way. In addition, the effective tip gap becomes much larger and allows higher leakage mass flow rate in comparison to the sharp-edge tip (i.e. a tip at the beginning of its operational life). The tip leakage losses are found much higher for the round-edge cavity tip (i.e. a tip exposed to burn-out effect). Experimental and computational flow visualisations, surface pressure measurements and discharge coefficient variation are given and analysed for several pressure ratios across the tip gap.

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“…In the passive flow control methods such as casing treatment (Houghton et al 2012;Sakuma et al 2014;Du et al 2016), blade tip winglet (Han et al 2014(Han et al , 2016 and blade tip modifications (Gourdain et al 2009;Ma et al 2012;Jung et al 2016), the geometrical change always works among the whole operating range and it may lead to a decrease of compressor performance near the design condition. For the active flow control techniques such as plasma actuation (Saddoughi et al 2015;Ashrafi et al 2016), tip injection (Li et al 2015;Grosvenor et al 2015;Khaleghi et al 2016) and casing aspiration (Lee et al 1990;Gmelin et al 2011;Grimshaw et al 2015), however, it can act on the flow fields flexibly either all the time or only when it is needed. As one of the effective active flow control methods, the suction technique attracts the attention from an increasing number of researchers to improve the flow fields in compressors.…”

Section: Introductionmentioning

confidence: 99%

Control of Tip Leakage Flow in Axial Flow Compressor Cascade by Suction on the Blade Tip

Mao

Liu

Tang

2018

JAFM

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One of the important ways of improving axial compressor performance is to control the tip leakage flow near the endwall region. Numerical computations were conducted to investigate the impact of blade tip suction on the axial compressor cascade performance in current paper. Three suction schemes located on the blade tip with different chordwise coverage were investigated in total. The results show that the cascade overall performance can be effectively enhanced by the proper suction scheme on the blade tip and the best scheme should be arranged at slightly downstream of the onset point of the tip leakage vortex (TLV). The control effectiveness and mechanisms are different for the different suction schemes. For the suction scheme covering the starting point of TLV, the onset point of TLV is shifted downstream, while an additional induced leakage flow near the blade leading edge is generated resulting in the increase of mixing loss. It is more effective when the structure of the main TLV is destroyed and divided into different parts by applying the blade tip suction arranged slightly behind the onset point of TLV. In addition, the blade loading is redistributed near the blade tip after the blade tip suction and the total pressure loss caused by the suction slots should also be considered in the design process.

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Delay of Rotating Stall in Compressors Using Plasma Actuators

Cited by 24 publications

References 31 publications

Control of Tip Leakage in a High-Pressure Turbine Cascade Using Tip Blowing

Control of Tip Leakage in a High-Pressure Turbine Cascade Using Tip Blowing

Effect of in-service burnout effect on the transonic leakage flows over cavity tip model

Control of Tip Leakage Flow in Axial Flow Compressor Cascade by Suction on the Blade Tip

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