A design strategy for a 6:1 supersonic mixed-flow compressor stage

Sadagopan, Aravinth; Camcı, Cengiz

doi:10.1016/j.ast.2019.02.026

Cited by 12 publications

(2 citation statements)

References 4 publications

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“…The impeller meridional discharge angle, α z2 , was chosen to be located between 50 • and 90 • . This range was selected based on the relatively well performing mixed flow compressors developed by Giri et al (2016), Kock (2017) and Sadagopan and Camci (2019a) for a similar operating mass flow rate. The lower bound for α z2 was chosen based on the research of Sadagopan and Camci (2019b), which suggests that more axial designs are not likely to attain the desired pressure ratio requirements in a single (compact) stage.…”

Section: Design Type Choicesmentioning

confidence: 99%

A Large Design Space Multidisciplinary Optimization of a Mixed Flow Micro Gas Turbine Compressor Stage

Ochabski

Spuy

Hildebrandt³

2020

Volume 8: Industrial and Cogeneration; Manufacturing Materials and Metallurgy; Marine; Microturbines, Turbochargers, and Small

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A parametrization method for the simultaneous optimization of the impeller and diffuser of a mixed flow compressor stage across a wide geometrical diversity is presented. The optimization focused on determining the optimal mixed flow (meridional) angle for a predefined set of constraints. The number of parameters required to achieve the large geometric diversity associated with a variable mixed flow angle was greatly reduced by coupling the endwall and camber Bézier control points with user-defined functions. The influence of geometric features on design performance was assessed using a Pearson correlation coefficient map. It was observed that stage total-to-static pressure ratio, and efficiency, were strongly influenced by diffuser outlet passage height and diffuser vane wrap angle. This was due to these parameters’ control of flow separation magnitude at the diffuser hub in the radial-to-axial bend. The method improved design point efficiency by 4.24 percentage points (to 86.24%) and increased the operating range by 6.7% at the cost of a decreased design point pressure rise, when compared to the baseline design.

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Section: Design Type Choicesmentioning

confidence: 99%

A Large Design Space Multidisciplinary Optimization of a Mixed Flow Micro Gas Turbine Compressor Stage

Ochabski

Spuy

Hildebrandt³

2020

Volume 8: Industrial and Cogeneration; Manufacturing Materials and Metallurgy; Marine; Microturbines, Turbochargers, and Small

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“…They conducted rotor design evaluation studies for 3.5 kg/s mass flow by performing mean-line code and computational analysis based on Bezier curves. They stated that a higher hub load would result in a higher performance of the impeller with a lower tip leakage loss and regular flow at the outlet [25]. Sadagopan et al computationally evaluated a supersonic mixed-flow compressor stage with a high-pressure ratio of 6:1 and an efficiency of 75.5%.…”

Section: Introductionmentioning

confidence: 99%

Analysis and Optimization of the Performances of the Tandem Blade Radial Compressor Using the CFD

Soylemez,

Behçet,

Parlak

2024

Applied Sciences

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Centrifugal compressors are frequently used in both military and commercial areas because they can be easily manufactured and reach high-pressure compression ratios. The factor that limits the performance and operating range of compressors is flow instability. Many ideas have been put forward for performance improvement, but tandem blade radial compressors, which do not require an extra air system, have attracted the most interest. In this study, computational fluid dynamics (CFD) analyses were carried out on various parameters of the tandem blade (TB) radial compressor, and an optimization study was carried out to find the best design using a genetic algorithm on a whole operating curve. It was investigated how these parameters affected the efficiency and total pressure ratio between the determined lower and upper limits. The numerical analyses of the optimum design obtained as a result of the iterations were carried out. As a result of the iterations, three optimum designs were obtained and numerical analysis was carried out according to one of them, and then they were compared with the results in the literature. The general agreement of computational fluid dynamics and the literature data served as a validation for the computational approach. The error rates between the numerical analysis results and the experimental results in the literature were calculated for different flow rates and were found to be 1.98% as the highest and 0.35 as the lowest. The work carried out in this article will provide a valuable reference for future advanced tandem blade compressor designs.

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Parametric modeling method for integrated design and manufacturing of radial compressor impeller

Zhou

Song

Xing

et al. 2020

Int J Adv Manuf Technol

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A design strategy for a 6:1 supersonic mixed-flow compressor stage

Cited by 12 publications

References 4 publications

A Large Design Space Multidisciplinary Optimization of a Mixed Flow Micro Gas Turbine Compressor Stage

A Large Design Space Multidisciplinary Optimization of a Mixed Flow Micro Gas Turbine Compressor Stage

Analysis and Optimization of the Performances of the Tandem Blade Radial Compressor Using the CFD

Parametric modeling method for integrated design and manufacturing of radial compressor impeller

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