RANS Simulations for Sensitivity Analysis of Compressor Transition Duct

Milanović, Ivana; Whiton, John; Florea, Razvan; Lynch, Steven; Tillman, Gregory; Hardin, Larry W.; Stucky, Mark

doi:10.2514/6.2014-3631

Cited by 5 publications

(4 citation statements)

References 7 publications

(12 reference statements)

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“…The results show a good agreement between the simulated and measured flow velocities, except near the casing wall at x=L = 1 where the CFD simulation over-predicts velocity magnitudes. A similar local discrepancy at the S-duct exit was also observed by Milanovic et al (2014), albeit on a strutted version of the baseline model; they attributed it to the shortcomings of the turbulence models. Note that, in the absence of error statistics for the measurements (Britchford et al, 1994;Britchford, 1998), the significance of this local discrepancy between the simulated values and the reported measurements cannot be quantified.…”

Section: Model Validation 331 Simulationsupporting

confidence: 70%

“…In this context, Britchford et al (1994) compared the k-e turbulence model and the Reynolds stress model, and reported that the mean velocity profile and shear stress are predicted better by the latter. Milanovic et al (2014) carried out RANS simulations for detailed sensitivity analysis of strutted compressor ducts, with the k-v and Spalart-Almaras turbulence models. Their computational predictions indicated good agreement with experimental data.…”

Section: Boundary Conditions and Submodel Selectionmentioning

confidence: 99%

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Shape optimization of annular S-ducts by CFD and high-order polynomial response surfaces

Immonen

2018

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Purpose This paper aims to design an optimal shape for an annular S-duct, considering both energy losses and exit flow uniformity, starting from a given baseline design. Moreover, this paper seeks to identify the design factors that affect the optimal annular S-duct designs. Design/methodology/approach The author has carried out computational fluid dynamic (CFD)-based shape optimization relative to five distinct numerical objectives, to understand their interrelations in optimal designs. Starting from a given baseline S-duct design, they have applied control node-induced shape deformations and high-order polynomial response surfaces for modeling the functional relationships between the shape variables and the numerical objectives. A statistical correlation analysis is carried out across the optimal designs. Findings The author has shown by single-objective optimization that the two typical goals in S-duct design, energy loss minimization and exit flow uniformity, are mutually contradictory. He has presented a multi-objective solution for an optimal shape, reducing the total pressure loss by 15.6 per cent and the normalized absolute radial exit velocity by 34.2 per cent relative to a baseline design. For each of the five numerical objectives, the best optimization results are obtained by using high-order polynomial models. Research limitations/implications The methodology is applicable to axisymmetric two-dimensional geometry models. Originality/value This paper applies a recently introduced shape optimization methodology to annular S-ducts, and, it is, to the author’s knowledge, the first paper to point out that the two widely studied design objectives for annular S-ducts are contradictory. This paper also addresses the value of using high-order polynomial response surface models in CFD-based shape optimization.

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Section: Model Validation 331 Simulationsupporting

confidence: 70%

Section: Boundary Conditions and Submodel Selectionmentioning

confidence: 99%

Shape optimization of annular S-ducts by CFD and high-order polynomial response surfaces

Immonen

2018

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“…3a, and it could be understood that excluding small discrepancies near to both walls, predicted simulation and experimental results matched quite well. However, similar discrepancies were also reported by the Milanvoic et al and Immonen [40,42] because of the improper handling of the wall curvature by the turbulence model. Duenas [15] had also commented that it might be difficult the accurate prediction of flow under the highly curved wall surface by Boussinesq eddy-viscosity turbulence models.…”

Section: Numerical Methods Validationsupporting

confidence: 78%

Design optimization of S-shaped compressor transition duct using particle swarm optimization algorithm

Sharma

Baloni

2020

SN Appl. Sci.

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A high-bypass turbofan engine transfers air from low-to the high-pressure compressor through an S-shaped transition duct. Minimization of the total pressure loss and maximization of uniform flow are key factors to ensure the maximum performance of the S-shaped transition duct. The conventional design approach is time-consuming and does not guarantee an optimal solution. Hence, the present article is based on the application of optimization for the S-shaped compressor transition duct. The optimization is carried out on the basis of shape parameters to minimize objectives namely pressure loss coefficient and non-uniformity with the reduction of length of the S-shaped transition duct. The 2-D axisymmetric approach of computational fluid dynamics is used as a design tool for performance evaluation with optimization techniques. The simulation model is validated with the available experimental results of the literature. The correlation between the response and independent variables is established with the help of the second-order polynomial response surface methodology. Further, individual optimization is carried out for single-objective consideration using particle swarm optimization and gray wolf optimization algorithms. As the results of single-objective optimization depict the conflicts between both objectives, later optimization using multi-objective particle swarm optimization and multi-objective gray wolf optimization algorithms is carried out. The performance metrics are obtained and compared. The 'TOPSIS' method is applied to get best solution out of multiple solutions. The optimized duct reduced pressure loss coefficient and non-uniformity index by 28.14% and 43.33% with a reduction of 6.37% of length compared to baseline S-shaped duct.

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“…The loss coefficient increased from 0.040 to 0.042 for without compressor case whereas it increased from 0.035 to 0.038 with compressor case. Milanovic et al [43] Baloni et al [44] One, six and eight strut -Computational fluid dynamics showed the capability to capture the flow physics of the duct accurately under the strutted environment. -Similar to the experimental study, numerical simulation also captured wakes near to the trailing edge of the strut.…”

Section: Number Of Struts Remarkmentioning

confidence: 99%

Review on the aerodynamics of intermediate compressor duct

Sharma¹,

Baloni²

2020

JMES

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In a turbofan engine, the air is brought from the low to the high-pressure compressor through an intermediate compressor duct. Weight and design space limitations impel to its design as an S-shaped. Despite it, the intermediate duct has to guide the flow carefully to the high-pressure compressor without disturbances and flow separations hence, flow analysis within the duct has been attractive to the researchers ever since its inception. Consequently, a number of researchers and experimentalists from the aerospace industry could not keep themselves away from this research. Further demand for increasing by-pass ratio will change the shape and weight of the duct that uplift encourages them to continue research in this field. Innumerable studies related to S-shaped duct have proven that its performance depends on many factors like curvature, upstream compressor’s vortices, swirl, insertion of struts, geometrical aspects, Mach number and many more. The application of flow control devices, wall shape optimization techniques, and integrated concepts lead a better system performance and shorten the duct length. This review paper is an endeavor to encapsulate all the above aspects and finally, it can be concluded that the intermediate duct is a key component to keep the overall weight and specific fuel consumption low. The shape and curvature of the duct significantly affect the pressure distortion. The wall static pressure distribution along the inner wall significantly higher than that of the outer wall. Duct pressure loss enhances with the aggressive design of duct, incursion of struts, thick inlet boundary layer and higher swirl at the inlet. Thus, one should focus on research areas for better aerodynamic effects of the above parameters which give duct design with optimum pressure loss and non-uniformity within the duct.

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RANS Simulations for Sensitivity Analysis of Compressor Transition Duct

Cited by 5 publications

References 7 publications

Shape optimization of annular S-ducts by CFD and high-order polynomial response surfaces

Shape optimization of annular S-ducts by CFD and high-order polynomial response surfaces

Design optimization of S-shaped compressor transition duct using particle swarm optimization algorithm

Review on the aerodynamics of intermediate compressor duct

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