Experimental Investigation of Rotating Instability in an Axial Compressor with a Steady Swirl Distortion Inlet
Abstract
:1. Introduction
2. Experimental Equipment and Scheme
2.1. Brief Introduction of the Compressor Test Bench
2.2. Swirl Distortion Generator
2.3. Experimental Methods
3. Results and Discussion
3.1. Description of the Swirl Flow
3.2. Compressor Performance
3.3. Effects on Stall Inception
3.4. Rotating Instability with Paired Swirl Distortion Inlet
4. Conclusions
- Due to the existence of the paired swirl distortion, the initial development of the compressor stall involved the alternation of short-scale disturbance and long-scale disturbance. The long-scale disturbance in the counter-rotating swirl sector propagated along the direction of the rotor rotation and was suppressed in the non-swirl and co-rotating swirl sectors, turning into short-scale disturbance or even disappearing, until the counter-rotating swirl sector was reached in the next revolution, and the disturbance strengthened again. Once the co-rotating swirl no longer restrained the development of the disturbance, the compressor rapidly entered the stall.
- In the case of the paired swirl distortion inlet, the obvious RI mainly existed in the counter-rotating swirl sector.
- For the compressor with a 2 mm rotor clearance, both paired swirl distortions with αst = ±20° and αst = ±40° induced RI. Compared with the RRI in the case of a clean inlet, when αst = ±20°, RRI increased by 69.8%, and when αst = ±40°, RRI increased by 135.8%.
- As the rotor clearance increased to 3 mm, the paired swirl distortion with αst = ±20° had different effects on RI at different circumferential positions. The counter-rotating swirl part strengthened the RI, and the RRI increased significantly, with a maximum value of 7.79, while the co-rotating part suppressed the RI, and the RRI decreased, reaching the value of 4.45.
- The enhancement and weakening effect of the paired swirl distortion on RI were attributed to the generation and suppression of shedding vortices at the rotor blade tip. In the compressor with a 3 mm rotor clearance, the co-rotating swirl inhibited the formation of shedding vortices and ameliorated the flow field of the rotor tip, thus delaying the stall. However, in the compressor with a 2 mm rotor tip clearance, the counter-rotating swirl deteriorated the flow field at the rotor tip, and the generation of shedding vortices induced RI, which promoted the advancement of the stall.
Author Contributions
Funding
Conflicts of Interest
Nomenclature
RI | Rotating instability |
BPF | Blade passing frequency/Hz |
Stagger angle of the swirl blades/° | |
Flow coefficient | |
Total to static pressure rise coefficient | |
Rotor tip clearance/mm | |
Static pressure/Pa | |
Mean static pressure/Pa | |
Density/kg·m−3 | |
Circumferential speed of rotor/m·s−1 |
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Related Parameter | Value |
---|---|
Rotational speed/r·min−1 | 1500 |
Rotor hub/tip ratio | 0.6 |
Blade numbers | 19/22 |
Aspect ratio at pitch diameter | 1.459/1.709 |
Tip clearance (1)/mm | 2/2 |
Tip clearance (2)/mm | 3/2 |
Design Parameters | Value |
---|---|
Chord length, mm | 100 |
Blade height, mm | 200 |
Camber angle, ° | 20 |
Profile | Naca65 series |
Inlet Condition | Sensor 1 | Sensor 2 | Sensor 3 | Sensor 4 | Sensor 5 | Sensor 6 | Sensor 7 | Sensor 8 |
---|---|---|---|---|---|---|---|---|
Clean | 6.48 | 4.13 | 3.96 | 7.90 | 12.51 | 14.69 | 9.45 | 11.68 |
αst = ±20° | 10.35 | 7.19 | 5.84 | 7.11 | 8.23 | 10.24 | 17.25 | 16.54 |
Absolute increase | 3.86 | 3.06 | 1.88 | −0.79 | −4.28 | −4.45 | 7.79 | 4.86 |
Relative increase | 59.6% | 74.1% | 47.5% | −10.0% | −34.2% | −30.3% | 82.4% | 41.6% |
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Xu, R.; Hu, J.; Wang, X.; Jiang, C.; Ji, J. Experimental Investigation of Rotating Instability in an Axial Compressor with a Steady Swirl Distortion Inlet. Energies 2021, 14, 8057. https://doi.org/10.3390/en14238057
Xu R, Hu J, Wang X, Jiang C, Ji J. Experimental Investigation of Rotating Instability in an Axial Compressor with a Steady Swirl Distortion Inlet. Energies. 2021; 14(23):8057. https://doi.org/10.3390/en14238057
Chicago/Turabian StyleXu, Rong, Jun Hu, Xuegao Wang, Chao Jiang, and Jiajia Ji. 2021. "Experimental Investigation of Rotating Instability in an Axial Compressor with a Steady Swirl Distortion Inlet" Energies 14, no. 23: 8057. https://doi.org/10.3390/en14238057
APA StyleXu, R., Hu, J., Wang, X., Jiang, C., & Ji, J. (2021). Experimental Investigation of Rotating Instability in an Axial Compressor with a Steady Swirl Distortion Inlet. Energies, 14(23), 8057. https://doi.org/10.3390/en14238057