CFD analysis of performance characteristics of Y-shaped diffuser with combined horizontal and vertical offsets

Gopaliya, Manoj Kumar; Chaudhary, Kuldeep

doi:10.1016/j.ast.2010.02.008

Cited by 17 publications

(8 citation statements)

References 6 publications

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“…x L loss ( ) and non-uniformity index ( S io ) is selected as the responses which are shown by Eqs. (7) and (8), respectively [37]. The total stagnation pressure loss ( P oin − P oout ) is nondimensionalized by the dynamic head 0.5 U 2 of the flow and represented by , whereas S io is the ratio of the average velocity in the y-direction ( U y avg ) to inlet velocity.…”

Section: Problem Definitionmentioning

confidence: 99%

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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Section: Problem Definitionmentioning

confidence: 99%

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

Sharma

Baloni

2020

SN Appl. Sci.

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“…Lots of work has been done on the prediction of the uniformity with offsetting by keeping the inlet and outlet in two different horizontal planes. Offsetting basically changes the difference between the mean radius of inlet and outlet of S-duct and it can be concluded that an increase in the offsetting also enhances the exit losses in order to accommodate the increase in non-uniformity at the outlet [12,14]. Also, secondary flow and counterrotating vortices were induced due to strong curvature.…”

Section: Figure 5 Axial Variation Of Static Pressure Coefficientmentioning

confidence: 99%

“…-Lower surface was more prone to separation due to strong secondary flow. Gopaliya et al [12,14] Rectangular to semicircular S-duct -The coefficient of pressure recovery ( ), effectiveness and nonuniformity decreased with the increase of offsetting .…”

Section: Figure 5 Axial Variation Of Static Pressure Coefficientmentioning

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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“…Submarine outfall diffusers occupy 41 % of total brine disposal capacity due to high dilution capabilities [1]. Besides, submarine outfall systems and diffusers are mostly used in many industrial applications from jet engineers to manifold and air conditioning systems [2][3][4][5][6].…”

Section: Introductionmentioning

confidence: 99%

Fsi Analysis of Submarine Outfall

Gücüyen

Erdem

Gökkuş

2016

brod

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In the scope of this study, main pipe of the diffuser, risers, ports, internal and external environments forming the discharge system which is used in application are modelled by Finite Elements Analysis (FEA) program to obtain discharge and structural behaviour. The last two spans of the system (20 m) and four ports on these spans are investigated. While the diameter and geometry of the risers and ports remain constant, the diffuser pipe is modelled in three different ways. These are constant sectioned (Model 1), contracting with sharp edge entrance sectioned (Model 2) and gradually contracting sectioned (Model 3) respectively. Among them, only Model 1 is treated as Single Degree of Freedom (SDOF) system and it is simulated by FEA to verify FEA solver in the first place. After structural suitability is confirmed, rest of the models are analysed to determine reaction forces and stresses. The discharge is performed as unsteady external flow as well as steady external flow assumption which is widely used in external flow model in the literature. The discharge analyses are performed in two different ways to verify FEA program. Iterative method is accompanying to FEA program. As a result of this study, proper model for structural and discharge behaviour and external flow effects on discharge velocities are obtained.

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CFD analysis of performance characteristics of Y-shaped diffuser with combined horizontal and vertical offsets

Cited by 17 publications

References 6 publications

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

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

Review on the aerodynamics of intermediate compressor duct

Fsi Analysis of Submarine Outfall

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