Bleed-Induced Distortion in Axial Compressors

Grimshaw, S. D.; Pullan, Graham; Walker, T. K.

doi:10.1115/1.4030809

Cited by 17 publications

(11 citation statements)

References 9 publications

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“…Aerodynamic studies have shown that the impact of bleed can be beneficial in reducing the blockage effect that is dominant in the downstream stage of the compressor. This can improve the compressor stability when extracted uniformly/circumferentially as demonstrated by Grimshaw et al 13 that shows an improvement in the stall inception when the flow is extracted in front of the rotor. In a similar but CFD study, Gou et al 14 show that the extraction or bleeding brings about an increase in the stage isentropic efficiency, deterioration in the transport of the tip leakage flow to the rotor blade pressure side and a reduction in the blockage.…”

Section: Methodology and Engine Specificationmentioning

confidence: 87%

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Impact of compressed air energy storage demands on gas turbine performance

Igie

Abbondanza

Szymański

et al. 2020

Proceedings of the Institution of Mechanical Engineers, Part A:

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Industrial gas turbines are now required to operate more flexibly as a result of incentives and priorities given to renewable forms of energy. This study considers the extraction of compressed air from the gas turbine; it is implemented to store heat energy at periods of a surplus power supply and the reinjection at peak demand. Using an in-house engine performance simulation code, extractions and injections are investigated for a range of flows and for varied rear stage bleeding locations. Inter-stage bleeding is seen to unload the stage of extraction towards choke, while loading the subsequent stages, pushing them towards stall. Extracting after the last stage is shown to be appropriate for a wider range of flows: up to 15% of the compressor inlet flow. Injecting in this location at high flows pushes the closest stage towards stall. The same effect is observed in all the stages but to a lesser magnitude. Up to 17.5% injection seems allowable before compressor stalls; however, a more conservative estimate is expected with higher fidelity models. The study also shows an increase in performance with a rise in flow injection. Varying the design stage pressure ratio distribution brought about an improvement in the stall margin utilized, only for high extraction.

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Section: Methodology and Engine Specificationmentioning

confidence: 87%

“…This can improve the compressor stability when extracted uniformly/circumferentially as demonstrated by Grimshaw et al. 13 that shows an improvement in the stall inception when the flow is extracted in front of the rotor. In a similar but CFD study, Gou et al.…”

Section: Flow Extraction – Chargingmentioning

confidence: 87%

Impact of compressed air energy storage demands on gas turbine performance

Igie

Abbondanza

Szymański

et al. 2020

Proceedings of the Institution of Mechanical Engineers, Part A:

View full text Add to dashboard Cite

show abstract

“…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%

“…So far the studies about suction mainly concentrate on the control of the boundary layer separation on the blade SS (Song et al 2006;Guo et al 2010;Shi et al 2015b) or the three-dimensional (3D) separation in the hub corner (Sachdeva et al 2011;Pönick et al 2013;Guo et al 2008;Marsan et al 2015). Apart from some researches about the effects of bleeding system on the compressor performance (Leishman et al 2007a(Leishman et al , 2007b(Leishman et al , 2007cGrimshaw et al 2015Grimshaw et al , 2016, there are only several investigations of suction technique on the control of TLF to improve the compressor performance and stability (Gümmer et al 2008;Dobrzynski et al 2008;Shi et al 2015a). It is found that the flow fields in the tip region and operating range can be improved by the suction on the casing.…”

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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“…While the active flow control can be imposed on the flow fields flexibly either all the time or only when the compressor’s operating point moves dangerously close to the stall line, such as plasma actuation, 31–33 tip injection, 34–38 and aspiration/suction techniques. 39–44 At present, the researches about aspiration mainly focus on the control of the boundary layer separation on blade SS or the 3D separation in the hub corner, 45–50 and the results show that the performance of compressor cascade can be improved significantly by applying the suction method.…”

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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Bleed-Induced Distortion in Axial Compressors

Cited by 17 publications

References 9 publications

Impact of compressed air energy storage demands on gas turbine performance

Impact of compressed air energy storage demands on gas turbine performance

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

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

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