Flow Through Cascades of Slotted Compressor Blades

Mikolajczak, A. A.; Weingold, H. D.; Nikkanen, J. P.

doi:10.1115/1.3445300

Cited by 9 publications

(1 citation statement)

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“…The experimental results showed that the slot suppressed flow separation in the middle section of the blade but had no positive effect on corner flow control. 1 Mikolajczak et al 2 and Fottner 3 experimentally investigated flow fields in cascades with slotted blades, and the results showed that the flow loss control was not only unsatisfactory but also had a negative effect (the loss increased). Sturm et al 4 hypothesized that the low speed of the slot outlet caused these suboptimal results and proposed using an external air source to form jets to actively control the boundary layer on the blade suction surface, with the jet speed equivalent to the local mainstream speed and the jet direction as parallel to the mainstream direction as possible.…”

Section: Introductionmentioning

confidence: 99%

Corner separation control in compressor stators with jets from the blade leading edge

Zheng

Zhou

2023

Advances in Mechanical Engineering

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Corner separation occurs easily in highly loaded compressor stators. This paper proposes a novel slot inside the stator blade, with the slot inlet located at the blade leading edge and the slot outlet located at the suction surface, by using the momentum of the incoming flow to form a high velocity jet to control the development of the boundary layer on the blade suction surface. For 3D compressor cascades, the influence of the key geometrical slot parameters on the flow fields in the slot and cascade passage and the aerodynamic performance of the cascade were investigated with a numerical method. Then, the stator blades in a highly loaded compressor stage were slotted to improve the flow in the stator blade passages. The main results can be summarized as follows. The use of slotted blades in the cascade effectively suppresses corner separation. When the cascade inlet velocity is high or the inlet flow is at a positive attack angle, the separation control effect improves. In the highly loaded compressor stage, slotted stator blades considerably reduced the flow loss at the stator corner, and the stage efficiency increased over the entire flow rate range. Furthermore, two cascades with unslotted and slotted blades were tested. The experimental and numerical results were consistent, demonstrating that the total pressure loss coefficient of a cascade can be effectively reduced by slotting the blades in the cascade.

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Section: Introductionmentioning

confidence: 99%

Corner separation control in compressor stators with jets from the blade leading edge

Zheng

Zhou

2023

Advances in Mechanical Engineering

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Review on internal flow mechanism and control methods of axial flow compressor at low Reynolds number

REN,

LU,

WANG

et al. 2024

Chinese Journal of Aeronautics

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Control of the boundary layer on compressor blade suction surfaces with the momentum jet

2023

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The boundary layer thickness on a compressor blade suction surface increases rapidly under a adverse pressure gradient and even separates from the blade surface. This paper proposes a novel method for developing the slot inside the blade, with the inlet of the slot located at the leading edge of the blade and the outlet located at the suction surface, using the momentum of the incoming flow to form a high velocity jet to control the boundary layer on the suction surface. For a plane cascade with a diffusion factor of 0.45, the effects of the main slot parametres (such as the shape of the slot and the positions of the slot inlet and outlet) on the flow in the slot, the flow field and the aerodynamic performance of the cascade were investigated with a numerical method. When the aerodynamic performance of cascades with slotted and unslotted blades was compared, it was found that a reasonable slot structure can effectively inhibit the development of the boundary layer on the blade suction surface and greatly improve the aerodynamic performance of the cascade. Based on the influence of the slot parametres of the above cascade, the slot of a plane cascade with a diffusion factor of 0.60 was designed. The numerical calculation results show that the slotted cascade with a diffusion factor of 0.60 outperformed the slotted cascade with a diffusion factor of 0.45. This result showed that the higher the cascade load, the greater the performance improvement from slotting. Furthermore, the unslotted and slotted cascades were tested, and the test results agreed well with the calculations. The aerodynamic performance of the slotted cascade was better than that of the unslotted cascade, which verifies the accuracy of the calculation method and the feasibility of blade slotting for suppressing the development of boundary layers on suction surfaces and reducing flow loss.

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Flow Through Cascades of Slotted Compressor Blades

Cited by 9 publications

References 0 publications

Corner separation control in compressor stators with jets from the blade leading edge

Corner separation control in compressor stators with jets from the blade leading edge

Review on internal flow mechanism and control methods of axial flow compressor at low Reynolds number

Control of the boundary layer on compressor blade suction surfaces with the momentum jet

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