Flow Mechanism for Stall Margin Improvement via Axial Slot Casing Treatment on a Transonic Axial Compressor

Kuang, Haiyang; Chu, S. Wuli; Zhang, H.; Ma, Shuai

doi:10.18869/acadpub.jafm.73.239.27047

Cited by 5 publications

(4 citation statements)

References 10 publications

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“…Although there are some discrepancies in predicting the pressure ratio and efficiency characteristics, it is concluded from Figure 7 that the predicted flow field is highly similar to the experimental results. Furthermore, the application of the commercial CFD software NUMECA TM to predict the flow field of Rotor 67 with the Spalart-Allmaras turbulence model has been widely validated by many researchers [23][24][25]. Thus, the predicted results can be considered acceptable for the purposes of this paper.…”

Section: Numerical Methods and Validationmentioning

confidence: 98%

Implementation of Three-Dimensional Inverse Design and Its Application to Improve the Compressor Performance

et al. 2020

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The implementation of a three-dimensional viscous inverse design used for an axial compressor is introduced in this paper. The derivation process of the inverse design algorithm is also described in detail. Moreover, an improved blade update method and a modified relaxation factor are included to enhance the inverse design algorithm. The inverse design is built on an in-house inverse design module coupled with commercial Computational Fluid Dynamic (CFD) software NUMECATM. In contrast to analysis design, the pressure loading and the normal thickness distribution along the blade surfaces are prescribed during the process of inverse design. The numerical methods used to solve the flow field are verified using the experimental data of the transonic fan rotor NASA Rotor 67. A recovery test for the Rotor 67 is carried out to validate the developed three-dimensional inverse design tool. To explore the potential application of the inverse design system, it is then used to improve the aerodynamic performance of a transonic fan Rotor 67 and a multi-row compressor Stage 35 at a near peak efficiency point by reorganizing the pressure loading distribution on the blade surfaces.

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Section: Numerical Methods and Validationmentioning

confidence: 98%

Implementation of Three-Dimensional Inverse Design and Its Application to Improve the Compressor Performance

et al. 2020

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“…The mechanism of the stability improvement is due to the ability to eliminate the separation zone in the near-casing zone. Kuang et al, 16 Amin et al 17 and Liu et al 18 carried out unsteady numerical simulations to study the effect of the slot casing treatments with different parameters, and found some patterns. Vuong et al 19 used NASA Stage 37 as the study subject and propose the inclined oblique slots (INOS) casing treatment which can improve the compressor stability.…”

Section: Introductionmentioning

confidence: 99%

Effect of different axial deflected angles of reversed blade-angle slots on the axial flow compressor performance and stability

Zhang

Zhong

Wang³

et al. 2023

Proceedings of the Institution of Mechanical Engineers, Part A:

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The aim of the paper is to explore the influence of the reversed blade-angle slot casing treatment (RBSCT) and its axial deflected angle (ADA) on the compressor performance and stability, and to reveal the mechanism that the change in ADA of the RBSCT influences the effect to broaden the compressor stable working range. The NASA Rotor 35 is used as the object of the investigation, and four RBSCTs with ADA of −15°, −30°, −45° and −60° are designed and investigated by unsteady numerical simulation. The results show that as the absolute value of the axial deflected angle increases, the capacity to improve the compressor stability of the RBSCT increases and then decreases. The unsteadiness of the injection and suction flows formed by the reversed blade angle slot plays an important role in the removal of the low-velocity zone. When ADA is −30°, the unsteadiness amplitude of the injection and suction flows is significantly higher than those of the other three. Consequently, the RBSCT with −30° ADA obtains the maximum stall margin improvement of 17.41% and the maximum design point efficiency improvement of 1.06% among the four RBSCTs.

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“…See Tan et al (2010) for a review. Numerous researchers have investigated the mechanism, modelling and control methods for the instability, e.g., Moore and Greitzer (1985), Greitzer and Moore (1986), Moore and Greitzer (1986), Kuang et al (2017), Mirzabozorg et al (2017).…”

Section: Introductionmentioning

confidence: 99%

A Moore-Greitzer Model for Ducted Fans in Ground Effect

Jin¹,

Fu²,

Qian³

et al. 2020

JAFM

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Ducted fans are widely used in unmanned aerial vehicles due to their high propulsive efficiency and safety. The aerodynamics are complex within the vicinity of the ground, including takeoff , landing and hovering. In the present study, the aerodynamic stability of the ducted fan was studied with a modified Moore-Greitzer model to estimate and analyse the stability in ground effect. The model was validated and compared with threedimensional unsteady simulations. The results indicated that the rotating stall occurred for the ducted fan in ground effect. The model results can be used to guide the design and control of the vehicles, to ensure the stability and safety of both the ducted fan and vehicles.

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Flow Mechanism for Stall Margin Improvement via Axial Slot Casing Treatment on a Transonic Axial Compressor

Cited by 5 publications

References 10 publications

Implementation of Three-Dimensional Inverse Design and Its Application to Improve the Compressor Performance

Implementation of Three-Dimensional Inverse Design and Its Application to Improve the Compressor Performance

Effect of different axial deflected angles of reversed blade-angle slots on the axial flow compressor performance and stability

A Moore-Greitzer Model for Ducted Fans in Ground Effect

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