Influence of non-axisymmetric terms on circumferentially averaged method in fan/compressor

Wan, Ke; Jin, Hailiang; Jin, Donghai; Gui, Xingmin

doi:10.1007/s11630-013-0586-1

Cited by 7 publications

(3 citation statements)

References 5 publications

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“…The inviscid force model in present work, which is presented by Jin 26 and Wan, 29 is based on a large particle method. The inviscid blade force is divided into two parts, that is, F B 1 and F B 2 .…”

Section: The Time-marching Throughflow Methodsmentioning

confidence: 99%

“…For the second parts F B 2 , Wan 29 simulated controlled diffusion airfoils (CDA) blade shape under different flow conditions, and found that p true¯ has a similar distribution with ( p s + p p ) 2 , especially in the middle and rear part of the blade passage. The average static pressure p true¯ is then used to replace ( p s + p p ) 2 , so that F B x 2 and F B r 2 are written as…”

Section: The Time-marching Throughflow Methodsmentioning

confidence: 99%

See 1 more Smart Citation

A fast computational method of the aerodynamic performance of fan and booster with inlet distortion

Tao

Jin²,

Liu

et al. 2022

Proceedings of the Institution of Mechanical Engineers, Part C:

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A fast computational method of the aerodynamic characteristics of fan and booster with inlet distortion is developed in this paper. This method is based on a time-marching throughflow model, and the governing equations are circumferentially averaged Navier-Stokes equations. A model of distributed inviscid blade force and viscid blade force is adopted to reproduce the flow deflection and loss. The deviation angle and loss parameters are interpolated from a database which is extracted from 3-D simulation results of compressor with uniform inlet. After a validation case is performed, the aerodynamical performances of a multistage fan and booster with inlet radial and circumferential distortion are computed. The results show the predictive ability of this method, and the acceptable computational time cost indicates the future application potential of this method during the design stage of a new turbomachinery.

show abstract

Section: The Time-marching Throughflow Methodsmentioning

confidence: 99%

Section: The Time-marching Throughflow Methodsmentioning

confidence: 99%

A fast computational method of the aerodynamic performance of fan and booster with inlet distortion

Tao

Jin²,

Liu

et al. 2022

Proceedings of the Institution of Mechanical Engineers, Part C:

View full text Add to dashboard Cite

show abstract

“…The first one is to add a factor in adjusting variable incidence angles, which makes this model more exact for different incidence angles. Moreover, the other one is that the circumferential fluctuation source terms [23,24] should also be considered in the governing equation since they also contribute to the flow structure. the axial velocity at the midspan are compared in Figure 19.…”

Section: Model Analysis On the Transonic Conditionmentioning

confidence: 99%

Development of a Throughflow-Based Simulation Tool for Preliminary Compressor Design Considering Blade Geometry in Gas Turbine Engine

Liu

Wan²,

Jin

et al. 2021

Applied Sciences

Self Cite

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Gas turbine engines are highly intricate machines, and every component of them is closely associated with one another. In the traditional engine developing process, vast experiment tests are needed. To reduce unnecessary trials, a whole gas turbine engine simulation is extremely needed. For this purpose, a compressor simulation tool is now developed. Considering the inherent drawbacks of 0D analysis and 3D CFD (Computational Fluid Dynamics) calculation, the 2D throughflow method is an indispensable tool. Based on the circumferential average method (CAM), 3D Navier–Stokes is transformed into a 2D method. One phenomenon arising is that the lack of description about circumferential motion leads to the need for the blade force modeling in compressor simulation. Previous models are based on the assumption that flow passes through the average stream surface without entropy increasing, which is not applicable in the CAM. An improved model is proposed based on the result analysis from CAM and NUMECA method in a linear cascade. Whereafter, the model is applied in a highly loaded and low-speed fan, which has been tested for its performance characteristics. Utilizing the new model, the error of the adiabatic efficiency between CAM and experiment decreases from 4.0% to 1.0% and the accuracy of the mass flow, and pressure ratio remains unchanged. The time involved in the CAM simulation is nearly 70 times faster than that of the 3D simulation.

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A Review of Some Key Issues in CFD-Based Throughflow Simulation

Hu,

Tao,

Liu

2024

Lecture Notes in Electrical Engineering

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Influence of non-axisymmetric terms on circumferentially averaged method in fan/compressor

Cited by 7 publications

References 5 publications

A fast computational method of the aerodynamic performance of fan and booster with inlet distortion

A fast computational method of the aerodynamic performance of fan and booster with inlet distortion

Development of a Throughflow-Based Simulation Tool for Preliminary Compressor Design Considering Blade Geometry in Gas Turbine Engine

A Review of Some Key Issues in CFD-Based Throughflow Simulation

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