Numerical Investigation of End Wall Boundary Layer Removal on Highly Loaded Axial Compressor Blade Rows

Gümmer, Volker; Goller, M.; Swoboda, M.

doi:10.1115/1.2749297

Cited by 54 publications

(27 citation statements)

References 17 publications

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“…In other words, the numerical calculation can approximately reproduce the experimental results, and the discrepancy is small enough to be ignored. Therefore, the 8 compressor simulation without bleeding can be used as the baseline to study the influence of bleeding rates on the compressor overall performance at different rotation speeds by the numerical simulation.…”

Section: Analysis On the Reliability Of Numerical Simulationmentioning

confidence: 99%

“…Its intensity and range largely depended on the rate and bleeding location. By analyzing the loss and the performance of compressor after the end wall boundary layer removal, Gummer (8,9) found that the bleeding can effectively reduce the reverse-flow along the casing and blockage and loss in local region. All these previous studies have shown that it is very likely to improve compressor performance by studying air system bleeding.…”

Section: Introductionmentioning

confidence: 99%

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Numerical Research on the Safety and Performance of Transonic Compressor with Bleed Air at Multiple Operation State

Cui

Zhao

Liu

et al. 2014

Procedia Engineering

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Some provisions in CCAR 33 are directly and indirectly related with the air system of aircraft engines. To certificate the characteristics of air system is an important work for engine airworthiness. Requirements and instructions of air system are issued under the above provisions in CCAR 33. Air system is essential to the safe and reliable operation of the aircraft engines. The bleed air is drawn out from the compressors. The Sec. 33.66 in CCAR 33, which is referred to as "Bleed air system", presents requirements and instructions for the bleed air. Bleed air from the high pressure compressor has taken up 3-5% in the air system, which keeping on growing during recent decades. Therefore, in view of the importance of air system and the bleed location, a new bleeding method with more efficient use of the bleed air is very much needed. In this paper, air system bleed is used for flow control to explore the feasibility of improving compressor performance through removing stator corner separation by bleed air. The transonic single-stage axial compressor Stage35 of NASA is taken as the research object to study the impact of stator bleed rates on the performance of compressor at different rotation speeds. The numerical research shows that bleeding on the stator casing corner can effectively enhance the performance of compressor at different rotation speeds and improve stator flow field.

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Section: Analysis On the Reliability Of Numerical Simulationmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Numerical Research on the Safety and Performance of Transonic Compressor with Bleed Air at Multiple Operation State

Cui

Zhao

Liu

et al. 2014

Procedia Engineering

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“…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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“…It was shown that passive flow control using vortex generators can reduce total pressure losses by affecting the corner separation at the crossing of the wall and blade [2,3]. It was reported also that active flow control using blowing, suction or synthetic jets can decrease greatly the total pressure losses by removing the corner separation [4][5][6][7][8][9].…”

Section: Introductionmentioning

confidence: 99%

Numerical investigation of three-dimensional separation control in an axial compressor cascade

Djedai¹,

Mdouki²,

Mansouri³

et al. 2017

IJHT

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The aerodynamic performances of three-dimensional compressor cascade are mainly influenced by secondary flow effects, such as the cross flow on the side wall and the corner separation at the wall-blade junction. Often, these secondary flows can produce a blockage and losses in the blade passage. A numerical study of active flow control using blowing technique in a linear compressor cascade has been carried out, in order to eliminate the 3D boundary layer stall and enhance the aerodynamic performance. The numerical simulation is performed using steady and incompressible RANS (Reynolds averaged Navier-Stokes) equations with Realizable k-ε turbulence model. Good agreement is found between numerical results and experimental data, in particular pressure coefficient (CP) and total pressure loss coefficient (). A detailed flow topology analysis is mentioned and gave the flow structure and the separation zone behavior. It was found that the blowing slot should be located upstream the dual nature critical point which represents the origin of separation. Furthermore, three suction slot configurations are used to control the separation, whereas one configuration on the suction side of the blade and two configurations are on the endwall. The first endwall slot is located parallel to the suction side of the blade and the second one is located perpendicular to the axial chord of the blade. Results indicate that the removal of the corner separation was not achieved using the slots on the blade suction side and on the endwall parallel to the suction side. Contrariwise, the perpendicular endwall slot was found to be most effective and the 3D separation is completely disappeared.

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Numerical Investigation of End Wall Boundary Layer Removal on Highly Loaded Axial Compressor Blade Rows

Cited by 54 publications

References 17 publications

Numerical Research on the Safety and Performance of Transonic Compressor with Bleed Air at Multiple Operation State

Numerical Research on the Safety and Performance of Transonic Compressor with Bleed Air at Multiple Operation State

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

Numerical investigation of three-dimensional separation control in an axial compressor cascade

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