Aerodynamics of swept and leaned transonic compressor-rotors

Benini, Ernesto; Biollo, Roberto

doi:10.1016/j.apenergy.2007.03.003

Cited by 80 publications

(39 citation statements)

References 13 publications

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“…The forward sweep was found to improve both the efficiency and the stall margin. Similar trend of the shock front movement and the efficiency increment was captured in the Rotor 37 case [17,18]. Denton and Xu [19] applied sweep to a transonic fan, where the stall margin was significantly extended due to the optimized shock structure.…”

Section: Introductionmentioning

confidence: 56%

Mechanisms of Sweep on the Performance of Transonic Centrifugal Compressor Impellers

Zheng

2017

Applied Sciences

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Featured Application: The mechanism for the optimal sweep angle of centrifugal compressors has been proposed, which benefits high-efficiency designs of centrifugal compressors for turbocharger and gas turbine engine applications.Abstract: Transonic centrifugal compressors with high performance are required in the oil and gas industries, modern gas turbine engines, and turbochargers. The sweep of the blades is one of the crucial features that have a significant influence on their performance. This paper numerically investigates mechanisms by which sweep affects the performance of a transonic impeller with twin splitters. Sweep is defined as scaling up or down the shroud chord, and the variation range of the sweep angle has been chosen from −25 to +25 • . In the current case, results show that the variation of choke mass flow rate, pressure ratio, and efficiency value is around 1%. If the centrifugal compressor has a higher pressure ratio or a higher front loading, the sweep effect on compressor performance will be even stronger. The essential aerodynamic effect of sweep is the spanwise redistribution of the front loading, resulting in effects on the shock structure, the tip leakage vortex, and the flow separation. On the shroud section, forward sweep restricts the front loading, the shock strength, and the tip leakage vortex, which reduces the loss near the casing. On the hub section, aft sweep suppresses the front loading and the flow separation, which reduces the loss near the hub. It is the delicate balance between controlling the loss near the hub and the loss near the casing that determines the optimal sweep angle design.

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Section: Introductionmentioning

confidence: 56%

Mechanisms of Sweep on the Performance of Transonic Centrifugal Compressor Impellers

Zheng

2017

Applied Sciences

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“…Maximum camber location effect was studied by Chen et al [69]. Benini [53] defined blade section profiles by Bezier curve using multi-objective optimization considering total pressure ratio and adiabatic efficiency as objectives for design of a compressor blade. He employed camber line and thickness profile as design parameters.…”

Section: Applications Of Surrogate Based Optimization Methodsmentioning

confidence: 99%

Surrogate Based Optimization Techniques for Aerodynamic Design of Turbomachinery

Samad¹,

Kim²

2009

International Journal of Fluid Machinery and Systems

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Recent development of high speed computers and use of optimization techniques have given a big momentum of turbomachinery design replacing expensive experimental cost as well as trial and error approaches. The surrogate based optimization techniques being used for aerodynamic turbomachinery designs coupled with Reynolds-averaged NavierStokes equations analysis involve single-and multi-objective optimization methods. The objectives commonly tried to improve were adiabatic efficiency, pressure ratio, weight etc. Presently coupling the fluid flow and structural analysis is being tried to find better design in terms of weight, flutter and vibration, and turbine life. The present article reviews the surrogate based optimization techniques used recently in turbomachinery shape optimizations.

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“…6. Blade axial curvature impact on shock, suction side boundary layer and blade wake development (Biollo & Benini, 2008a) A recent numerical work gave another point of view on the impact of blade curvature in transonic compressor rotors, showing how the movement of blade sections in the axial direction can influence the internal flow field (Benini & Biollo, 2007;Biollo & Benini, 2008a). Such work showed that the axial blade curvature can help to influence the shock shape in the meridional plane, inducing the shock to assume the meridional curvature of the blade leading edge (Fig.…”

Section: Three-dimensional Shaped Bladingsmentioning

confidence: 99%