Effect of inlet distortion on the performance of axial transonic contra-rotating compressor

Liu, Hanru; Wang, Yangang; Hu, Wenbin

doi:10.1177/0954410016670421

Cited by 12 publications

(4 citation statements)

References 20 publications

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“…5 that the difference between the curves (three investigated cases) is higher at higher rotational speeds (except for 100% speed line in which SCM has higher computational errors). It is worth to mention that the prior research such as Liu et al (2016), Naseri and Boroomand (2016), mainly focused on a specific rotational speed, and no study has been conducted for different revolution. Effects of inlet distortion on fan efficiency are also shown in Fig.…”

Section: Resultsmentioning

confidence: 99%

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Investigation of inlet distortion effects on axial compressor performance based on streamline curvature method

Abbasi

Pirnia

Taghavi-Zenouz

2018

jtam

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In this paper, the effects of inlet flow distortion on performance maps and details of the flow field are investigated using the Streamline Curvature Method. The results are presented for both design and off-design conditions and compared with experimental data, which shows good agreement. The effects of inlet flow distortion are investigated by inlet total pressure variation in three different cases in the way that the average total pressure remains constant and equal to the design value. The results show that a relative increase in the total pressure at tip causes an increase in the pressure ratio and efficiency as well as a better performance in the choking region. Alternatively, a relative increase in the total pressure in hub causes opposite behavior and a better performance at the surging region.

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Section: Resultsmentioning

confidence: 99%

“…It has an important role on the stall inception process. Liu et al (2016) investigated the effect of inlet distortion on the performance of an axial transonic contra-rotating compressor by means of full-annulus simulation. Results revealed that the inlet distortion leads to reduction of the pressure ratio and efficiency.…”

Section: Introductionmentioning

confidence: 99%

Investigation of inlet distortion effects on axial compressor performance based on streamline curvature method

Abbasi

Pirnia

Taghavi-Zenouz

2018

jtam

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“…Furthermore, it was found that the effect of radial distortion on the stability of the fan was negligible. The effect of circumferential total pressure inlet distortion on the performance of a transonic contra-rotating compressor was numerically investigated by Liu et al 12 The interaction between the leakage flow and the detached shock wave at the leading edge of the rear rotor (and the ensuing blockage) was suggested to be one of the reasons for stall inception. Manas and Pradeep 13 investigated the effect of speed combination on stall inception in a contra-rotating fan.…”

Section: Introductionmentioning

confidence: 99%

A theory for rotating stall in contra-rotating fans

Khaleghi

Shahriyari

Heinrich

2020

Proceedings of the Institution of Mechanical Engineers, Part C:

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This paper reports on a theory of rotating stall in contra-rotating fans and compressors. The theory is developed from Moore’s theory. A second-order hysteresis is used in the current study for the pressure rise of the counter-rotating rows. This enables the model to predict the transient behavior of the stall cell. Comparing the experimental results with the theory shows that the modified model can predict the speed of the stall cells fairly accurately. Results show that the rotor speed ratio plays a critical role in the stall cell speed and its direction of rotation. Furthermore, the developed model makes it possible to study the effects of stagger angle and number of stall cells. The conditions under which pure rotating stall can occur in contra-rotating fans are also discussed in this paper. It is shown that the stall cells merge to form a single cell before a stable fully-developed rotating stall is established.

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“…The steady three-dimensional vortex structure of stator under transition conditions was established, and the mechanism of the stalling process was revealed from the perspective of the vortex structure evolution. Liu et al 22 conducted numerical investigation to reveal that the inlet distortion deteriorates the performance of both the upstream and downstream rotors resulting in reduction of total pressure ratio, efficiency, and stall margin of the transonic contrarotating compressor. To improve the flow in transonic compressor, Hu and Wang 23 proposed a compressor design concept by increasing the axial velocity of the rotor outlet to reduce the degree of reaction for the sake of avoiding the flow separation.…”

Section: Introductionmentioning

confidence: 99%

Numerical investigation on the shock-wave and flow structures in a transonic contra-rotating axial compressor

Liu

Wang

Zhang

2017

Advances in Mechanical Engineering

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Numerical simulation has been conducted on a transonic contra-rotating axial compressor to investigate the shock wave and flow characteristics under various operation conditions. Results indicate that the shock-wave structure in the downstream rotor (Rotor 2) of transonic contra-rotating axial compressor is more complex than that in the upstream rotor (Rotor 1). Under the choke condition, a double shock-wave structure appears in the Rotor 2 leading to serious loss. Moving to the design condition, a single shock wave appears at the root and middle sections of blade of Rotor 2, while a normal and an oblique shock wave arise at the blade tip. Under the near-stall condition, the shock structure has no obvious difference from other conditions at the blade root of Rotor 2 but it becomes further off-body at the middle blade. During the switch of transonic contra-rotating axial compressor from the choke to the near-stall condition, the separation bubble on the pressure surface of Rotor 2 decreased gradually due to the increasing aerodynamics load. The suction surface experiences the weakest separation at the design point. Alternatively, the tip leakage flow becomes stronger with maximum loss at the near-stall condition. The radial matching of the meridional passage of Rotor 2 with the routing flow parameters is the potential optimization aspect.

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Effect of inlet distortion on the performance of axial transonic contra-rotating compressor

Cited by 12 publications

References 20 publications

Investigation of inlet distortion effects on axial compressor performance based on streamline curvature method

Investigation of inlet distortion effects on axial compressor performance based on streamline curvature method

A theory for rotating stall in contra-rotating fans

Numerical investigation on the shock-wave and flow structures in a transonic contra-rotating axial compressor

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