Aerodynamic Instabilities of Swept Airfoil Design in Transonic Axial-Flow Compressors

He, Chen; Ma, Yuduan; Liu, Xiaohua; Sun, Dakun; Sun, Xiaofeng

doi:10.2514/1.j056053

Cited by 27 publications

(5 citation statements)

References 56 publications

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“…Denton et al 31 suggested that the effect of sweep blade on transonic fan efficiency and total pressure ratio was remarkably small, but forward sweep blade could significantly improve compressor stall margin compared with backward sweep blade. He et al 32,33 investigated the effects of a swept airfoil design on the transonic compressor stall margin based on a new stall inception prediction approach, and they found the backward sweep would obviously deteriorate the compressor stability; unfortunately, the forward sweep rotor did not show remarkable influence on the stall margin. Considering the combination of rotor sweep design and casing treatment, Song et al 32 explored the design and optimization of circumferential casing grooves considering sweep and lean variations on the blade tip, and the results showed that sweep introduced to the tip alters the interactions of grooves and blade.…”

Section: Introductionmentioning

confidence: 99%

“…He et al 32,33 investigated the effects of a swept airfoil design on the transonic compressor stall margin based on a new stall inception prediction approach, and they found the backward sweep would obviously deteriorate the compressor stability; unfortunately, the forward sweep rotor did not show remarkable influence on the stall margin. Considering the combination of rotor sweep design and casing treatment, Song et al 32 explored the design and optimization of circumferential casing grooves considering sweep and lean variations on the blade tip, and the results showed that sweep introduced to the tip alters the interactions of grooves and blade. They suggested that the combination of sweep and casing grooves was promising to obtain a better compressor performance.…”

Section: Introductionmentioning

confidence: 99%

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Study on the combined influence of aerodynamic sweep and casing treatment in a transonic compressor rotor

Chi,

Chu,

Zhang

2023

Proceedings of the Institution of Mechanical Engineers, Part G:

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Casing treatment and three-dimensional blade design are effective techniques to remedy the deficiency of compressor stability margin, yet their combined effects on compressor performance are seldom studied. With the help of URANS simulations, this paper explored the combined influence of aerodynamic sweep and casing treatment in a transonic compressor rotor. Compared with the configurations of single sweep and single casing treatment, the combined configuration presented an outstanding advantage for improving compressor performance. For compressor overall performance, the stall margin improvement of combined configuration was up to 11.8%, larger than single forward sweep and single casing treatment. Meanwhile, peak efficiency penalty of combined configuration (−1.02%) was significantly lower than that of single casing treatment. Under the effect of casing treatment, the results showed that the pulsating axial velocity could effectively delay the interface of the tip leakage flow and main flow, preventing the overflow of tip leakage flow. The distributions of blockage coefficient and loading coefficient indicated that combined configuration was more effective due to tip unload by casing treatment and blockage resistance ability by forward sweep. Furthermore, the spatial and temporal evolutions of axial velocity at slot opening surface were discussed in detail. Compared with the single casing treatment, higher positive axial velocity excitation and smaller range of negative axial velocity were introduced by combined configuration, which contributed to better stability enhancement.

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Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Study on the combined influence of aerodynamic sweep and casing treatment in a transonic compressor rotor

Chi,

Chu,

Zhang

2023

Proceedings of the Institution of Mechanical Engineers, Part G:

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“…Xu 23 added an additional part of blade force to consider the viscosity on the blade surface. He et al 24 improved the blade force model, and assumed that the loss force is proportional to the relative flow kinetic energy. Hill and Defoe 25 proposed a blade force model based on single-passage simulation results and experimental data.…”

Section: Introductionmentioning

confidence: 99%

A fast computational method of the aerodynamic performance of fan and booster with inlet distortion

Tao

Jin²,

Liu

et al. 2022

Proceedings of the Institution of Mechanical Engineers, Part C:

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A fast computational method of the aerodynamic characteristics of fan and booster with inlet distortion is developed in this paper. This method is based on a time-marching throughflow model, and the governing equations are circumferentially averaged Navier-Stokes equations. A model of distributed inviscid blade force and viscid blade force is adopted to reproduce the flow deflection and loss. The deviation angle and loss parameters are interpolated from a database which is extracted from 3-D simulation results of compressor with uniform inlet. After a validation case is performed, the aerodynamical performances of a multistage fan and booster with inlet radial and circumferential distortion are computed. The results show the predictive ability of this method, and the acceptable computational time cost indicates the future application potential of this method during the design stage of a new turbomachinery.

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“…Vad et al (2015) comprehensively described the characteristics of forward-swept blades. Combining straight blades and forward-swept blades can increase the efficiency of the fan by 2-3%, although for free-vortex rotors, there is little improvement in efficiency (He et al, 2018;Kaya et al, 2018).…”

Section: Introductionmentioning

confidence: 99%

Structure and Topology Analysis of Separated Vortex in Forward-Swept Blade

Liang

Zhou

et al. 2021

Front. Energy Res.

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Flow separation commonly affects the stability of turbomachines, especially under low-flowrate conditions. Compared with conventional blades, a forward-swept blade is more efficient at high flowrates. However, experiments and numerical simulations show that a forward-swept blade produces an unstable region under low flowrate. In this paper, the topological analysis is used to analyze the structure and size of flow separation in forward swept blades. Three-dimensional structure and formation mechanism of vortices in forward-swept blades are analyzed using the cross-section flow pattern method. For forward-swept blades, flow separation mainly occurs at the blade tip and corner, accompanied by clear velocity fluctuations, the break-up of shed vortices, and diffusion. With decreasing flowrate, the shedding vortices move forward and the speed of vortex annihilation gradually decreases. In addition, the number of singularities in the rotor passage increases with the decrease of flow rate, and the region affected by shedding vortex increases. The rotating direction of internal vortex in turbomachinery is fixed. The pressure surface, passage vortex, and concentrated shedding vortex were found to rotate clockwise, whereas the suction surface, corner vortex, and shedding vortex rotate in a counterclockwise direction.

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Aerodynamic Instabilities of Swept Airfoil Design in Transonic Axial-Flow Compressors

Cited by 27 publications

References 56 publications

Study on the combined influence of aerodynamic sweep and casing treatment in a transonic compressor rotor

Study on the combined influence of aerodynamic sweep and casing treatment in a transonic compressor rotor

A fast computational method of the aerodynamic performance of fan and booster with inlet distortion

Structure and Topology Analysis of Separated Vortex in Forward-Swept Blade

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