Numerical Investigation for the Impact of Single Groove on the Stall Margin Improvement and the Unsteadiness of Tip Leakage Flow in a Counter-Rotating Axial Flow Compressor

Mao, Xiaochen; Liu, Bo; Zhao, Hao

doi:10.3390/en10081153

Cited by 5 publications

(2 citation statements)

References 46 publications

(55 reference statements)

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“…Cevik et al [15] studied circumferential grooves with a saw tooth shape. Houghton and Day [16,17], Sakuma et al [18], and Mao et al [19] investigated the influence of the position and size of a single square groove on the compressor performance. Sakuma et al [18] found that a groove located at 0.2 axial chords from the leading edge of the blade was the best position for this design feature.…”

Section: Introductionmentioning

confidence: 99%

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Effect of a Recirculating Type Casing Treatment on a Highly Loaded Axial Compressor Rotor

Kawase

Rona

2019

IJTPP

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The tip leakage flow over the blades of an axial compressor rotor adversely affects the axial rotor efficiency and can determine the onset of tip leakage stall. The performance of a new casing treatment concept in the shape of an axisymmetric recirculation channel is explored by steady Reynolds-Averaged Navier–Stokes (RANS) realizable k-ε modelling on the NASA Rotor 37 test case. The modelling exposed a number of attractive features. The casing treatment increased the stall margin at no penalty to the rotor isentropic efficiency over the rotor operating line. A recirculation in the casing channel self-activated and self-adjusted with the rotor loading to provide more passive flow control at higher rotor loading conditions. The nozzle-shaped recirculation channel outflow opposed the tip leakage jet, re-located the casing surface flow interface further downstream, and reduced the rotor blade tip incidence angle. This combination of features makes the new casing treatment particularly attractive for applications to high thrust-to-weight ratio engines, typical of high-performance jet aircraft.

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Section: Introductionmentioning

confidence: 99%

“…Sakuma et al [18] found that a groove located at 0.2 axial chords from the leading edge of the blade was the best position for this design feature. Mao et al [19] numerically showed that the circumferential groove also improves the operating range of an advanced counter-rotating axial flow compressor.…”

Section: Introductionmentioning

confidence: 99%

Effect of a Recirculating Type Casing Treatment on a Highly Loaded Axial Compressor Rotor

Kawase

Rona

2019

IJTPP

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Investigation of the casing groove location effect for a large tip clearance in a counter-rotating axial flow compressor

Mao

Liu

2020

Aerospace Science and Technology

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Experimental investigation on stall characteristics of contra-rotating compressor with variable speed ratios

et al. 2021

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By experiment at a low-speed large-scale axial contra-rotating compressor, the near stall points of 19 speed configurations were captured and the stall characteristics under different speed ratios were obtained successfully. The results show that the compressor with speed ratio greater than 1 are more likely to stall than the compressor with speed ratio less than 1 and the flow rate at the starting point of stall is at least 18% earlier, the pressurization capacity is at least 5.5% higher when speed values of the front and rear rotors are interchanged. At the same speed ratio, the dimensionless characteristic lines of pressure rise coefficient-flow coefficient almost coincide. With the decrease of speed ratio, the dimensionless characteristic line of contra-compressor moves upward. Through summing up all speed configurations' stall types and stall initial disturbance frequency, it can be found that: there is a critical speed ratio between 1.125 and 1.167 in the contra-rotating compressor studied in this paper. When the speed ratio is less than the critical value, the stall disturbance has the characteristic like spike stall. At this time, the initial stall disturbance frequency is higher with the speed ratio is smaller. And at the same speed ratio, the initial stall disturbance frequency increases with the increase of the average speed of the front and rear rotors. When the speed ratio is greater than the critical value, the stall disturbance doesn't rotate circumferentially.

show abstract

Numerical Investigation for the Impact of Single Groove on the Stall Margin Improvement and the Unsteadiness of Tip Leakage Flow in a Counter-Rotating Axial Flow Compressor

Cited by 5 publications

References 46 publications

Effect of a Recirculating Type Casing Treatment on a Highly Loaded Axial Compressor Rotor

Effect of a Recirculating Type Casing Treatment on a Highly Loaded Axial Compressor Rotor

Investigation of the casing groove location effect for a large tip clearance in a counter-rotating axial flow compressor

Experimental investigation on stall characteristics of contra-rotating compressor with variable speed ratios

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