Aerodynamic performance of transonic axial compressor with a casing groove combined with blade tip injection and ejection

Dinh, Cong-Τruong; Heo, Man-Woong; Kim, Kwang‐Yong

doi:10.1016/j.ast.2015.07.006

Cited by 34 publications

(20 citation statements)

References 18 publications

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“…Model 1 and model 2 stall margin is increased by 6.62 % and 4.45 % respectively. The stall margin achieved in the present study is higher than the stall margin reported by [33] and [11]. The bar chart of the adiabatic efficiency for models 1-2 and smooth wall casing is shown in Figure 13.…”

Section: Resultscontrasting

confidence: 65%

“…The efficiency of models 1-2 is reduced by 0.79 percent and 1.08 percent respectively. The adiabatic efficiencies achieved by model 1-2 is higher than the adiabatic efficiencies investigated by [33] and [11].…”

Section: Resultsmentioning

confidence: 54%

“…Xi et al [10] suggested new approach for the casing treatment for compressor stability. A parametric study is conducted by Dinh et al [11] to connect the circumferential grooves with the blade tip injection. The groove height, front length and rear length were selected as geometrical parameters.…”

Section: Introductionmentioning

confidence: 99%

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CFD Investigation of an Axial Compressor with Casing Treatment for the Enhancement of the Stall Margin

et al. 2021

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Casing treatment is an efficient technique which is used to increase the compressor stall margin with a minor reduction in the efficiency. The interaction between the blade passage and the groove is the main cause of the stall margin improvement by various researches. A numerical study is conducted on a single circumferential casing groove using NASA rotor 37 in the current study. The performance of the two circumferential groove models is studied by discretizing RANS 3D equations using a finite volume technique. The inception of the stall is predicted according to the criteria of convergence. Two models of the circumferential groove have been suggested and numerically tested. A single passage simulation is selected for the two models. The performance of the smooth casing and the two models are analyzed. Moreover, the stall margin, total pressure ratio and peak adiabatic efficiency of the normal casing, and the two models are analyzed to determine the influence of the groove on the axial compressor performance and stability. Models 1 and 2 stall margins are enhanced by 6.62 % and 4.45% respectively. The adiabatic efficiency of model 1 and model 2 are decreased by 0.79 % and 1.08 % respectively.

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Section: Resultscontrasting

confidence: 65%

Section: Resultsmentioning

confidence: 54%

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CFD Investigation of an Axial Compressor with Casing Treatment for the Enhancement of the Stall Margin

et al. 2021

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“…The experimental near stall point was at 0.925 of normalized mass flow rate, while the numerical near stall point was 0.921 of normalized mass flow rate, which was 0.43% of relative error. However, the numerical results using the two-equation k- turbulence model [15], [16] showed a very good agreement with the experimental data, where the relative errors between numerical and experimental results for total pressure ratio and efficiency were only 1% and 2%, respectively, and the relative error for the near-stall point between numerical simulation and experimental data was only journal.ump.edu.my/jmes ◄ 0.12%. So, the two-equation k- turbulence model with a scalable wall function was selected with y + values of the first nodes near the walls in a range from 20 to 100.…”

Section: Methodsmentioning

confidence: 81%

Effects of stator splitter blades on aerodynamic performance of a single-stage transonic axial compressor

Quang¹,

Le²,

Dinh³

2020

JMES

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Splitter blades located between stator blades in a single-stage axial compressor were proposed and investigated in this work to find their effects on aerodynamic performance and operating stability. Aerodynamic performance of the compressor was evaluated using three-dimensional Reynolds-averaged Navier-Stokes equations using the k-e turbulence model with a scalable wall function. The numerical results for the typical performance parameters without stator splitter blades were validated in comparison with experimental data. The numerical results of a parametric study using four geometric parameters (chord length, coverage angle, height and position) of the stator splitter blades showed that the operational stability of the single-stage axial compressor enhances remarkably using the stator splitter blades. The splitters were effective in suppressing flow separation in the stator domain of the compressor at near-stall condition which affects considerably the aerodynamic performance of the compressor.

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“…Three parameters, i.e., the total pressure ratio (PR), adiabatic efficiency (η), and stall margin (SM), were used to assess the aerodynamic performance and operational stability of the transonic compressor with and without the casing treatment [29,33,34]:…”

Section: Performance Parametersmentioning

confidence: 99%

Stability Enhancement of a Single-Stage Transonic Axial Compressor Using Inclined Oblique Slots

Vuong

Kim

2021

Energies

Self Cite

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A casing treatment using inclined oblique slots (INOS) is proposed to improve the stability of the single-stage transonic axial compressor, NASA Stage 37, during operation. The slots are installed on the casing of the rotor blades. The aerodynamic performance was estimated using three-dimensional steady Reynolds-Averaged Navier-Stokes analysis. The results showed that the slots effectively increased the stall margin of the compressor with slight reductions in the pressure ratio and adiabatic efficiency. Three geometric parameters were tested in a parametric study. A single-objective optimization to maximize the stall margin was carried out using a Genetic Algorithm coupled with a surrogate model created by a radial basis neural network. The optimized design increased the stall margin by 37.1% compared to that of the smooth casing with little impacts on the efficiency and pressure ratio.

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Aerodynamic performance of transonic axial compressor with a casing groove combined with blade tip injection and ejection

Cited by 34 publications

References 18 publications

CFD Investigation of an Axial Compressor with Casing Treatment for the Enhancement of the Stall Margin

CFD Investigation of an Axial Compressor with Casing Treatment for the Enhancement of the Stall Margin

Effects of stator splitter blades on aerodynamic performance of a single-stage transonic axial compressor

Stability Enhancement of a Single-Stage Transonic Axial Compressor Using Inclined Oblique Slots

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