CFD Investigation on the Application of Optimum Non-Axisymmetric Endwall
                        Profiling for a Vaned Diffuse

Li, Zhou; Fan, Xiaopeng; Wang, Z.

doi:10.29252/jafm.11.06.28664

Cited by 2 publications

(2 citation statements)

References 12 publications

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“…This was achieved through the optimization of the blade profile. Similar investigations were reported in literatures (Chen 2007;Huang 2019;Ennil et al 2018;Zhou et al 2018). Eq.…”

Section: Optimization Problemsupporting

confidence: 90%

Multi-Objective Optimization of Aerodynamic Performance for a Small Single-Stage Turbine

2022

JAFM

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In order to improve the performance of single-stage turbines, blade profiling optimization was conducted for the guide vane and rotor under design condition. Support vector regression (SVR) and non-dominated sorting genetic algorithm-II (NSGA-II) were used to execute the optimization, with the objective of maximizing the efficiency and total pressure ratio of single-stage turbines. The gas turbine chosen for the initial study was the KJ66, which is one of the most robust and primitive small gas turbine designs available. The influence mechanism of the stator and rotor profiling on flow field and performance was discussed. The results revealed that compared with the prototype, the adiabatic efficiency increased by 5.95% and the total pressure ratio increased by 0.9%. Furthermore, the matching of flows between the stator blade and rotor blade obviously improved. The optimized guide vane suppressed the flow separation by increasing the leading edge and improving the distribution of the inlet angle of attack. The load distribution of rotors with a 50% spanwise position changed from the original "C" loaded to post-loaded. The leading load obviously decreased, and the angle of attack was smaller than that of the prototype, which effectively weakened the flow separation at the leading edge of the rotor. Compared with the original rotor, the higher lean angle and pressure ratio of the turbine stage also improved. However, the leakage loss near the shroud of the rotor increased, which led to decreased efficiency.

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“…This was achieved through the optimization of the blade profile. Similar investigations were reported in literatures (Chen 2007;Huang 2019;Ennil et al 2018;Zhou et al 2018). Eq.…”

Section: Optimization Problemsupporting

confidence: 90%

Multi-Objective Optimization of Aerodynamic Performance for a Small Single-Stage Turbine

2022

JAFM

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“…Recently, nonaxisymmetric endwall contouring technology proved its effectiveness in turbines 16,17 and axil compressors [18][19][20] to suppress the secondary flow and flow separation. Zhou et al 21 performed a numerical optimization on non-axisymmetric contouring endwall for a vaned diffuser hub-side wall of a centrifugal compressor, which showed the total pressure loss of the diffuser decreased under design condition, but the stable operating range of compressor stage decreased as well. Hermann et al 22 utilized a hub-side endwall contouring technology on the vaned diffuser inlet region of an open impeller centrifugal compressor stage.…”

Section: Introductionmentioning

confidence: 99%

Numerical investigation of centrifugal compressor stability enhancement using vaned diffuser endwall contouring technology

Cui

Qin

Jia

et al. 2022

Energy Science & Engineering

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To improve the stable operating range of centrifugal compressor stage, endwall contouring technology is introduced on the hub-side wall of the vaned diffuser for NASA CC3 centrifugal compressor as a promising technique to redistribute the flow field near the endwall in this paper. The main contents of this paper are listed as follows. First, a specific parameterized endwall contouring guideline is developed based on sinusoidal function and Bézier curve, and three factors are considered, namely, peak height, peak radial position, and frequency coefficient. Then, centrifugal compressor stages with baseline diffuser and contoured endwall diffusers are numerically investigated to reveal the influence of endwall contouring on the stable operating range. Results show that endwall contouring is an effective method to achieve stability enhancement with no evident reduction in stage performance on the design point. CEW13-12 has the most successful combination of endwall contouring parameters, and stall margin is increased by up to 40% for CEW13-12. Finally, the influence mechanism of endwall contouring on the stable operating range is discussed. At the near stall condition, the contouring endwall forces the fluid within the semi vaneless space to deflect toward the suction side to increase the momentum of low-energy fluid in the suction surface boundary layer and reduce the adverse pressure gradient on the suction side, which delay the development of flow separation on the vane leading edge near the shroud side to suppress the onset of rotating stall. At the near choke condition, the contouring endwall has more potential to increase the throat area, resulting in a decrease of throat blockage to improve choke margin. The results show that the endwall contouring technology is a reliable method to achieve stability enhancement of centrifugal compressor stage.

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CFD Investigation on the Application of Optimum Non-Axisymmetric Endwall Profiling for a Vaned Diffuse

Cited by 2 publications

References 12 publications

Multi-Objective Optimization of Aerodynamic Performance for a Small Single-Stage Turbine

Multi-Objective Optimization of Aerodynamic Performance for a Small Single-Stage Turbine

Numerical investigation of centrifugal compressor stability enhancement using vaned diffuser endwall contouring technology

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