Numerical Investigation on Tandem Compressor Cascades

Payyappalli, Manas Madasseri; Shine, S. R.

doi:10.1115/gtindia2015-1311

Cited by 5 publications

(2 citation statements)

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“…Actually, even for the two dimensional (2D) tandem cascades, the configuration will impact the performance significantly. [9][10][11] Thus, there are large of studies about the configuration optimization of tandem cascades, [12][13][14][15][16][17][18][19] of these, Hergt and Siller explored the general design criteria for the subsonic and transonic tandem cascades based on a large database. 12,13,18 However, considering the strong three dimensional (3D) effect in compressors, the guidance obtained from 2D optimization is limited for 3D tandem blade design.…”

Section: Introductionmentioning

confidence: 99%

Coupling optimization design of configuration and swept-bowed effects in highly loaded subsonic compressor tandem cascades with tip clearance

Mao,

Jiao,

Cheng

et al. 2024

Proceedings of the Institution of Mechanical Engineers, Part G:

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The coupling optimization design for swept-bowed effects and configuration of tandem cascade is conducted in a highly loaded subsonic compressor tandem cascade, in which the novelty lies in considering the spanwise distribution of configuration parameters and exploring the coupling relationship between them and swept-bowed design. Research results show that, compared with the original one, the loss coefficient of the optimal tandem cascade is decreased by 38.7% at the 4° incidence angle and the range of available incidence angle expands by 25%. For the distribution of the configuration parameters, parameters at the hub are significantly different from those near the tip, which confirms the tandem blade design in compressors is complex and needs to consider 3D flow effect. Forward swept and positive bowed design are beneficial for reducing loss at tip and alleviating the blockage, which cannot be achieved by the optimization only for configuration parameters. In terms of the weak coupling relationship between configuration parameters distribution and swept-bowed effects, the former should be considered first in practical engineering.

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Section: Introductionmentioning

confidence: 99%

Coupling optimization design of configuration and swept-bowed effects in highly loaded subsonic compressor tandem cascades with tip clearance

Mao,

Jiao,

Cheng

et al. 2024

Proceedings of the Institution of Mechanical Engineers, Part G:

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“…In addition, the performance of the tandem cascade could not be improved only by adjusting the geometric parameters mentioned in the previous paragraph. Due to the coherent effect of front and rear blades, the incidence angle range with small loss of the tandem cascade may be reduced, 14 and the tandem airfoils are difficult to give full play to their potential. By introducing other flow control techniques, such as endwall contouring, 15 three-dimensional blade designs (bending and sweeping), 16 boundary layer suction, 17 the aerodynamic performance of tandem cascade in off-design states can be remarkably improved.…”

Section: Introductionmentioning

confidence: 99%

Study on flow separation and suction control of a compressor tandem cascade

Zhang

Mao

Liu

et al. 2023

Proceedings of the Institution of Mechanical Engineers, Part C:

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To control the boundary layer separation on the front blade suction surface in a compressor tandem cascade at a high incidence angle, three suction schemes at different axial positions were introduced and the cascade performance improvement and separation flow control effects were investigated. Based on the experimental and numerical simulations, the aerodynamic performance of the prototype tandem cascade reaches the peak at the incidence angle of 5°. Continue to increase the incidence angle, the loss increases sharply, and the static pressure rise coefficient and diffusion factor begin to decrease. With the boundary layer suction on the suction surface of the front blade, fluid energy in the upstream boundary layer of the suction slot is increased, and the adverse pressure gradient downstream is decreased. By suction, the development and separation of the boundary layer are inhibited, and the loss in the tandem cascade is significantly reduced. The flow control effect of the suction scheme at the onset location of boundary layer separation is the best, and the flow loss can be reduced by about 34.9% with a suction flow rate of 1% at the incidence angle of 5°. The suction schemes have good flow control effects in a wide working range and broaden the available range of incidence angles of the tandem cascade. This study provides a reference for the design of tandem blades considering flow control and has a positive significance for improving compressor efficiency and pressure ratio.

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