Unsteady Study on the Effects of Matching Characteristic of Tandem Cascade on the Performance and Flow at Large Angle of Attack

Liu, Hanru; Yue, Shaoyuan; Wang, Yangang; Zhang, Jun

doi:10.1007/s11630-018-1017-0

Cited by 10 publications

(7 citation statements)

References 8 publications

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“…As for the numerical method, the CFX software was used to solve the Reynolds average Naiver-Stokes equation (Akbarian et al, 2018). The two-equation SST turbulence model (Liu et al, 2018a(Liu et al, , 2018b was used combined with the two-equation γ -Re θ transition model (Menter et al, 2006;Langtry et al, 2006). Single-passage cascade was modeled to capture the flow structure.…”

Section: Numerical Methodologymentioning

confidence: 99%

Sensitivity investigation of a subsonic cascade performance to geometric deviations based on statistical method

Chen

Wang

Liu

et al. 2020

Engineering Applications of Computational Fluid Mechanics

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Section: Numerical Methodologymentioning

confidence: 99%

Sensitivity investigation of a subsonic cascade performance to geometric deviations based on statistical method

Chen

Wang

Liu

et al. 2020

Engineering Applications of Computational Fluid Mechanics

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“…This is a constructive effort to guide splitter blading design into becoming a conventional design process, which also provides a beneficial reference to developing an empirical model for tandem blades. In addition, Schlaps [10], Schneider [11], and Kumar [12,13] indicated that optimal design parameters may change in design and off-design conditions; for instance, a larger pitch-wise blade distance will lead to a simultaneous increase of the loss and choke margins [14]. The CFD-combined numerical optimization algorithm has been adopted in the tandem blade design, which presented further enhancements of blade performance: Ju [15] et al optimized a 2D tandem airfoil with a multiobjective genetic algorithm and an artificial neural network method; A. Hergt and U. Siller [16] pointed out several principles for transonic tandem blade design based on asynchronous multiobjective genetic algorithm results.…”

Section: Cfd Setup and Proceduresmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

A New Method for Rapid Optimization Design of a Subsonic Tandem Blade

Tao

Liu

2020

Applied Sciences

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Tandem blade technology has been developed for years due to its capacity to bear higher aerodynamics than conventional configurations. Even so, there is still the tough problem of how to design tandem blades effectively and further improve blade performance. This paper tries to further understand the flow characteristics of tandem blades in order to present a new method of designing them under subsonic inflow conditions. Firstly, efforts were made to reveal the aerodynamic interaction between the forward blade (FB) and the aft blade (AB). Secondly, considering this aerodynamic interaction, the design principles and the camber line modification method were put forward, with which typical controlled diffusion airfoil (CD airfoil) isentropic Mach number distributions can be achieved for both FB and AB. Lastly, the optimizations were conducted on a 2D tandem blade and a transonic compressor with a tandem blade, respectively. The computation fluid dynamic (CFD) results show that the optimized tandem blade achieves a significant improvement for both 2D blade performance and transonic compressor characteristics at low speeds.

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“…Meanwhile, the effects of other parameters, such as the chord ratio and camber ratio of the front-to-rear blades and the gap nozzle structure, on the performance of tandem cascades have also been studied in detail. 10–12…”

Section: Introductionmentioning

confidence: 99%

Study on flow separation and suction control of a compressor tandem cascade

Zhang

Mao

Liu

et al. 2023

Proceedings of the Institution of Mechanical Engineers, Part C:

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To control the boundary layer separation on the front blade suction surface in a compressor tandem cascade at a high incidence angle, three suction schemes at different axial positions were introduced and the cascade performance improvement and separation flow control effects were investigated. Based on the experimental and numerical simulations, the aerodynamic performance of the prototype tandem cascade reaches the peak at the incidence angle of 5°. Continue to increase the incidence angle, the loss increases sharply, and the static pressure rise coefficient and diffusion factor begin to decrease. With the boundary layer suction on the suction surface of the front blade, fluid energy in the upstream boundary layer of the suction slot is increased, and the adverse pressure gradient downstream is decreased. By suction, the development and separation of the boundary layer are inhibited, and the loss in the tandem cascade is significantly reduced. The flow control effect of the suction scheme at the onset location of boundary layer separation is the best, and the flow loss can be reduced by about 34.9% with a suction flow rate of 1% at the incidence angle of 5°. The suction schemes have good flow control effects in a wide working range and broaden the available range of incidence angles of the tandem cascade. This study provides a reference for the design of tandem blades considering flow control and has a positive significance for improving compressor efficiency and pressure ratio.

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Unsteady Study on the Effects of Matching Characteristic of Tandem Cascade on the Performance and Flow at Large Angle of Attack

Cited by 10 publications

References 8 publications

Sensitivity investigation of a subsonic cascade performance to geometric deviations based on statistical method

Sensitivity investigation of a subsonic cascade performance to geometric deviations based on statistical method

A New Method for Rapid Optimization Design of a Subsonic Tandem Blade

Study on flow separation and suction control of a compressor tandem cascade

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