Optimization of Tandem Blade Based on Improved Particle Swarm Algorithm

Song, Zhaoyun; Liu, Bo; Mao, Xiaochen; Xia, Lu

doi:10.1115/gt2016-56901

Cited by 6 publications

(5 citation statements)

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“…В результаті оптимізації авторам вдалося знизити втрати повного тиску на 20%. Результати, представлені в роботі [5], присвячені оптимізації конструкції дворядного лопаткового вінця. Поряд з підвищенням напірності ступеня компресора, авторам вдалось досягти підвищення ККД завдяки оптимізації кута повороту потоку.…”

Section: аналіз попередніх досліджень і публікаційunclassified

Моделювання Течії В Дворядному Вентиляторі Турбореактивного Двоконтурного Двигуна

Балалаев¹,

Балалаева²,

Терещенко³

2021

aktt

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Modern trends in the global aircraft industry are prompting aircraft engine engineers to create and develop various methods to improve the aerodynamic characteristics of turbomachines. The urgent need to improve the efficiency of new generation engines leads to a rapid increase in the bypass ratio of engines, which requires the development of fans with large diametrical dimensions and high aerodynamic perfection. Boundary layer control in turbomachines using tandem blade rows is one of the most promising ways to improve the aerodynamic characteristics of aircraft engine fans with a high bypass ratio. The work aims to evaluate the aerodynamic characteristics of a fan with a tandem impeller for a turbofan engine. Two fan impellers were investigated: a single-row and an equivalent tandem-row (the equivalence was ensured by the equality of the structural angles of the flow inlet and outlet and the equality of the chord of the profiles). The blade row consisted of 33 blades, the tip diameter at the inlet to the impeller was 2.37 m, the hub diameter was 0.652 m. The flow was simulated in the range of axial velocity at the inlet from 80 to 200 m/s at a relative rotor speed of 0.65, 0.85, and 0.9. For the investigated tandem fan impeller, the chord of the first row was 60% of the total chord of the profile, the length of the slotted channel was 10% of the total chord. The flow was simulated using a numerical experiment. When closing the system of Navier-Stokes equations, Menter's SST turbulence model was used. The computational grid is unstructured, with an adaptation of the boundary layer. The work shows that the use of a tandem impeller will improve the aerodynamic characteristics of the fan. As a result of the study, it was found that the pressure ratio in a fan with tandem impeller increases from 0.32 to 20% for an operating mode at a relative rotor speed of n=0.65, n=0.85, and n=0.9 in the range of values of the gas-dynamic flow rate function q (λ)=0.4...1. The greatest growth is observed on the left branches of the pressure lines. The obtained data on the efficiency of a fan with a tandem impeller showed that in the range of values of the gas-dynamic flow rate function q(λ)=0.4...0.6 and q(λ)=0.76...0.98 a tandem impeller is higher than the efficiency of a fan with a single-row impeller, for values of the gas-dynamic flow function q(λ)=0.64...0.76 - the efficiency of a fan with a tandem impeller is 4% less than the efficiency of a fan with a single-row impeller.

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Section: аналіз попередніх досліджень і публікаційunclassified

Моделювання Течії В Дворядному Вентиляторі Турбореактивного Двоконтурного Двигуна

Балалаев¹,

Балалаева²,

Терещенко³

2021

aktt

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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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“…On the basis of CFD, several strategies have been applied for the optimization. Both genetic algorithms (GAs) [6] [7] and particle swarm optimization (PSO) methods [8] [9] are widely used. In addition, surrogate-based optimization (SBO) [5] [10] and Artificial Neural Network (ANN) [11] [12] become popular recently in the aerodynamic shape optimization of turbomachinery.…”

Section: Introductionmentioning

confidence: 99%

Aerodynamic Optimization of a Centrifugal Fan Using Response Surface Methodology

Liu¹,

Zhang²,

Li³

et al. 2019

OJFD

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In this paper, the optimization scheme of a centrifugal fan under the constraints of the total pressure difference, efficiency and shaft power was carried out. The blade inlet angle β 1A and the blade outlet angle β 2A of the centrifugal impeller were optimized using the Response Surface Methodology (RSM). Nine optimization cases were presented. The aerodynamic performance and the flow field of the optimized model were carefully compared with the original model. The results show that the total pressure difference and the total-pressure efficiency increase by 5.7% and 4.2% respectively after the optimization. Compared with the original fan, the flow field inside the impeller of the optimized fan has been improved. The flow separation existing around the blade suction surface outlet is suppressed significantly. For fields in the volute, the optimization scheme has reduced the local vortex intensity and weakened the vortex scale. The flow field stability around the volute tongue is also correspondingly improved.

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Optimization of Tandem Blade Based on Improved Particle Swarm Algorithm

Cited by 6 publications

References 0 publications

Моделювання Течії В Дворядному Вентиляторі Турбореактивного Двоконтурного Двигуна

Моделювання Течії В Дворядному Вентиляторі Турбореактивного Двоконтурного Двигуна

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

Aerodynamic Optimization of a Centrifugal Fan Using Response Surface Methodology

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