A time-marching throughflow model and its application in transonic axial compressor

Jin, Hailiang; Jin, Donghai; Li, Xiaojuan; Gui, Xingmin

doi:10.1007/s11630-010-0418-5

Cited by 19 publications

(13 citation statements)

References 11 publications

(12 reference statements)

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“…A better result has been shown by Simon 40 and Jin et al. 41 However, besides a better prediction of endwall effects that can be obtained by using Navier–Stokes based model, a major reason for the better agreement is that these calculations take advantage of information extracted from the 3D simulations, as for instance, the deviation angle distribution. Considering the more general approach used here, the results obtained are therefore very satisfactory.…”

Section: Applicationsmentioning

confidence: 84%

Time-marching throughflow analysis of multistage axial compressors based on a novel inviscid blade force model

Yang

et al. 2019

Proceedings of the Institution of Mechanical Engineers, Part G:

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A time-marching throughflow method for the off-design performance analysis of axial compressors is described. The method is based on the Euler equations, and a new inviscid blade force model is proposed in order to achieve desired flow deflection. The flow discontinuity problems at the leading and trailing edges are tackled by automatic correction of blade mean surface using cubic spline interpolation. Empirical loss models have been integrated into the throughflow model in order to simulate the viscous force effects in the real three-dimensional flow. Two test cases have been presented to validate the throughflow model, including the transonic fan rotor – NASA Rotor 67 working at a near-peak-efficiency point and a 1.5-stage high-speed axial compressor with inlet guide vane operating at 68% nominal speed. Reasonable flow parameters distributions have been obtained in the Rotor 67 fan calculating results, and accurate overall performance characteristics have also been predicted at the strong off-design condition for the 1.5-stage axial compressor. The CPU time of both cases cost less than one minute at one operating point. The results indicate that the developed time-marching throughflow model is effective and efficient in the turbomachinery performance analysis.

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Section: Applicationsmentioning

confidence: 84%

Time-marching throughflow analysis of multistage axial compressors based on a novel inviscid blade force model

Yang

et al. 2019

Proceedings of the Institution of Mechanical Engineers, Part G:

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“…The no-slip condition is applied at solid boundaries. The detailed solving process to the governing equations are described in the author's previous work [16]. This throughflow model has been applied to predict the performance of a transonic fan, ATS-2.…”

Section: Methodsmentioning

confidence: 99%

A Novel Viscous Throughflow Model for Compressor Analysis and Its Application

Jin¹,

Dao-bin²,

Yin³

2020

IJFMTS

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“…A time-marching finite volume method is chosen to solve equations. The validation of CAM by NASA Rotor 67 and a high-loaded low speed fan TA36 can be found in references [31,32]. More details for CAM can also be reviewed in references [33,34].…”

Section: Numerical Model and Research Objectmentioning

confidence: 99%

Investigation of Seal Cavity Leakage Flow Effect on Multistage Axial Compressor Aerodynamic Performance with a Circumferentially Averaged Method

Jin

Gui

2021

Applied Sciences

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The seal cavity leakage flow has a considerable impact on the performance of the aeroengine, especially on the multistage compressor. Thus, a quasi-three-dimensional simulation program named CAM is developed basing on circumferentially averaged throughflow method. The program enables a rapid diagnosis for the performance degradation of multistage compressor caused by labyrinth wear. The coupling flow field between the seal cavity leakage flow and the main flow field at the root of the shrouded stator of a high-loading three-stage compressor with inlet guide vanes (IGV) was simulated by CAM and the results indicate that seal cavity leakage flow has a significant impact on the overall performance of the compressor. That is, for a 1% increase in the seal-tooth clearance-to-span ratio, the decrease in total pressure ratio was 2.6%, and the reduction in efficiency was 0.6%. Stage performance shows that the seal cavity leakage flow reduces the pressurization capacity of the current stator and the work capacity of the downstream rotor, but has little effect on the upstream blade row. Spanwise distribution of blade element performance shows that the leakage flow leads to an increased flow blockage near the hub, resulting in spanwise migration. The incidence of the stator and rear rotor then change through the entire span. The leakage flow leads to the flow blockage and migration and hence changes the incidence angle, which results in the deterioration of compressor performance.

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A time-marching throughflow model and its application in transonic axial compressor

Cited by 19 publications

References 11 publications

Time-marching throughflow analysis of multistage axial compressors based on a novel inviscid blade force model

Time-marching throughflow analysis of multistage axial compressors based on a novel inviscid blade force model

A Novel Viscous Throughflow Model for Compressor Analysis and Its Application

Investigation of Seal Cavity Leakage Flow Effect on Multistage Axial Compressor Aerodynamic Performance with a Circumferentially Averaged Method

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