Research on three-dimensional blade designs in an ultra-highly loaded low-speed axial compressor stage: Design and numerical investigations

Yu, Xin; Liu, Baojie

doi:10.1177/1687814016674629

Cited by 11 publications

(5 citation statements)

References 42 publications

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“…In addition, the stator hub is stationary while the rotor rotates at 1100 RPM. More detailed design parameters of the compressor can be seen in Yu [15].…”

Section: Investigated Compressormentioning

confidence: 99%

Numerical Investigation of the Effect of Hub Gaps on the 3D Flows Inside the Stator of a Highly Loaded Axial Compressor Stage

Zhu

Qiu

et al. 2022

Energies

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Both the compressor performance and the 3D flows inside the stator passage are significantly impacted by the stator hub gap. The interplay between leakage flow and corner separation within a cantilevered stator of a highly loaded, low-speed axial compressor with a succession of stator hub gaps was examined numerically in this paper. Firstly, the simulated results were compared with the measured results, including the compressor characteristics, the 3D flow structures, and the flow fields at the stator outlet. The results revealed that the used CFD solver, as well as the corresponding setup, can reproduce the flow not only in terms of the trend along with the stator hub gap, but also in terms of the specific scale of the 3D flow structure. Hence, it is feasible enough to be applied in the present investigation. Secondly, the flow mechanisms of the interplay between the corner separation and the leakage flow with different stator hub gaps were analyzed. It was found that the velocity of the leakage flow is the key parameter that dominates the flow structures as well as the compressor performance. Additionally, a simple metric was proposed to be used to choose the optimum stator hub gap. By comparing our results with those from published research, this metric was proven to be feasible. Finally, it is also discussed how the stator hub gap affected the stator inlet flow and rotor performance. It is demonstrated that the stator passage flow blockage can affect the upstream flow field. As a result, the performance of the rotor tends to vary in the opposite direction to that of the stator.

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“…In addition, the stator hub is stationary while the rotor rotates at 1100 RPM. More detailed design parameters of the compressor can be seen in Yu [15].…”

Section: Investigated Compressormentioning

confidence: 99%

Numerical Investigation of the Effect of Hub Gaps on the 3D Flows Inside the Stator of a Highly Loaded Axial Compressor Stage

Zhu

Qiu

et al. 2022

Energies

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“…The nominal rotor tip clearance was kept to be 1% blade height, while the nominal stator hub clearance is varied at 0.0%, 0.25%, 0.5%, and 1.0% blade height, which will be denoted as 0.00τ, 0.25τ, 0.50τ and 1.00τ, respectively. More detailed design parameters are summarized in Table 1, which were also introduced in [28][29][30].…”

Section: Experiments Setupmentioning

confidence: 99%

Experimental Investigation of the Flow Mechanisms and the Performance Change of a Highly Loaded Axial Compressor Stage with/without Stator Hub Clearance

Liu

Qiu

et al. 2019

Applied Sciences

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Three-dimensional corner separation is common in axial compressors, which can lead to large flow loss and blockage especially when it evolves into the corner stall (open separation). In this paper, the evolution of the three-dimensional flow structures inside a cantilevered stator of a 1.5 stage low-speed highly loaded axial compressor as the stator hub clearance varies, and its effect on the whole compressor performance are investigated experimentally. Firstly, when the stator hub is sealed, the hub corner stall will occur at small mass flow rate conditions. Then, when a very small stator hub clearance is introduced, the leakage flow tends to strengthen the hub corner separation at large mass flow rate conditions and prompts the occurrence of hub corner stall as the mass flow rate decreases. This is mainly caused by the fact that the leakage flow has relatively low energy due to the viscosity effect in the clearance and large flow loss generation as the clearance flow comes across and mixes with the transverse secondary flow. Finally, when the stator hub clearance increases, the effect of the flow viscosity becomes very weak and could be ignored, so the enhanced leakage flow can suppress the transverse migration of the low energy flow near the hub, and the hub corner separation at large mass flow rate conditions could be weakened and the hub corner stall at small mass flow rate conditions could be removed or delayed. As the stator hub clearance varies, the flow structures inside the stator passage could be summarized into five typical flow structures, and this is closely associated with the performance of the compressor.

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“…30 The effects of three-dimensional bladings in an ultra-highly loaded compressor stage were studied numerically by Yu and Liu. 31 All of the above assumptions are based on experience and may result in designing a stage where the occurrence of stall is probable. In this paper, we have presented a developed method for determining the degree of reaction for each stage considering the effect of flow coefficient, stage loading, work-done factor, and also the effect of blade geometry such as camber angle, stagger angle and, finally, the blade solidity.…”

Section: Introductionmentioning

confidence: 99%

Improved criteria for stall-free preliminary design of axial compressor of aero gas turbine engines

Aligoodarz

Mehrpanahi

Moshtaghzadeh

et al. 2018

Proceedings of the Institution of Mechanical Engineers, Part G:

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A worldwide effort has been devoted to developing highly efficient and reliable gas turbine engines. There exist many prominent factors in the development of these engines. One of the most important features of the optimal design of axial flow compressors is satisfying the allowable range for various parameters such as flow coefficient, stage loading, the degree of reaction, De-Haller number, etc. But, there are some applicable cases that the mentioned criteria are exceeded. One of the most famous parameters is De-Haller number, which according to literature data should not be kept less than 0.72 in any stage of the axial compressor. A deep insight into the current small- or large-scale axial flow compressors shows that a discrepancy will occur among design criterion for De-Haller number and experimental measurements in which the De-Haller number is less than the design limit but no stall or surge is observed. In this paper, an improved formulation is derived based on one-dimensional modeling for predicting the stall-free design parameter ranges especially stage loading, flow coefficient, etc. for various combinations. It was found that the current criterion is much more accurate than the De-Haller criterion for design purposes.

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Research on three-dimensional blade designs in an ultra-highly loaded low-speed axial compressor stage: Design and numerical investigations

Cited by 11 publications

References 42 publications

Numerical Investigation of the Effect of Hub Gaps on the 3D Flows Inside the Stator of a Highly Loaded Axial Compressor Stage

Numerical Investigation of the Effect of Hub Gaps on the 3D Flows Inside the Stator of a Highly Loaded Axial Compressor Stage

Experimental Investigation of the Flow Mechanisms and the Performance Change of a Highly Loaded Axial Compressor Stage with/without Stator Hub Clearance

Improved criteria for stall-free preliminary design of axial compressor of aero gas turbine engines

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