Prestall Behavior of a Transonic Axial Compressor Stage via Time-Accurate Numerical Simulation

Chen, Jen‐Ping; Hathaway, Michael D.; Herrick, Gregory P.

doi:10.21236/ada500494

Cited by 14 publications

(12 citation statements)

References 11 publications

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“…In the passage of the two rotor blade rows, there exists a distinguishable attached oblique passage shock, which originates from the leading edge of the rotor blade and extends across the passage to 80% chord on the suction surface of the adjacent blade. This is comparable to the results at steady state by Chen et al 22 In addition, similar to Figure 7, the static pressure distribution is basically axisymmetric in the circumferential direction in the front blade rows, but there is still some nonaxisymmetric distribution in the rear blade rows as well as in the clearance between rotor and stator. In the clearance between adjacent blade rows, the flow field is affected by both the upstream and downstream blades.…”

Section: Numerical Analysis Of the Full-annulus Flow Fieldsupporting

confidence: 90%

Numerical simulation of the non-uniform flow in a full-annulus multi-stage axial compressor with the harmonic balance method

Sun

Wang

et al. 2020

Advances in Mechanical Engineering

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To improve the understanding of unsteady flow in modern advanced axial compressor, unsteady simulations on full-annulus multi-stage axial compressor are carried out with the harmonic balance method. Since the internal flow in turbomachinery is naturally periodic, the harmonic balance method can be used to reduce the computational cost. In order to verify the accuracy of the harmonic balance method, the numerical results are first compared with the experimental results. The results show that the internal flow field and the operating characteristics of the multi-stage axial compressor obtained by the harmonic balance method coincide with the experimental results with the relative error in the range of 3%. Through the analysis of the internal flow field of the axial compressor, it can be found that the airflow in the clearance of adjacent blade rows gradually changes from axisymmetric to non-axisymmetric and then returns to almost completely axisymmetric distribution before the downstream blade inlet, with only a slight non-axisymmetric distribution, which can be ignored. Moreover, the slight non-axisymmetric distribution will continue to accumulate with the development of the flow and, finally, form a distinct circumferential non-uniform flow field in latter stages, which may be the reason why the traditional single-passage numerical method will cause certain errors in multi-stage axial compressor simulations.

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Section: Numerical Analysis Of the Full-annulus Flow Fieldsupporting

confidence: 90%

Numerical simulation of the non-uniform flow in a full-annulus multi-stage axial compressor with the harmonic balance method

Sun

Wang

et al. 2020

Advances in Mechanical Engineering

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“…They simulated a NASA single-stage compressor rotor that consists of 36 blade passages, shown in Figure 5. TURBO, which is "a physics-based simulation tool for multistage turbomachinery" [14], was used to solve the Navier-Stokes equations (details of which can be found in [15]) in a full-annulus model. Each blade passage (as seen in Figure 5) was modeled using a curvilinear grid of dimensions 151 × 71 × 56 (in general, x × y × z ).…”

Section: Reducing the Storage Size Of A Computational Fluid Dynamics mentioning

confidence: 99%

Using the Nonuniform Dynamic Mode Decomposition to Reduce the Storage Required for PDE Simulations

Hall

Chou

Chen

2019

International Journal of Aerospace Engineering

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Partial Differential Equation simulations can produce large amounts of data. These datasets are very slow to transfer, for example, from an off-site supercomputer to a local research facility. There have been many model reduction techniques that have been proposed and utilized over the past three decades. Two of the most popular techniques are the Proper Orthogonal Decomposition and Dynamic Mode Decomposition. Nonuniform Dynamic Mode Decomposition (NU-DMD) is one of the newest techniques as it was introduced in 2015 by Guéniat et al. In this paper, the NU-DMD’s mathematics are explained in detail, and three versions of the NU-DMD’s algorithm are outlined. Furthermore, different numerical experiments were performed on the NU-DMD to ascertain its behavior with respect to errors, memory usage, and computational efficiency. It was shown that the NU-DMD could reduce an advection-diffusion simulation to 6.0075% of its original memory storage size. The NU-DMD was also applied to a computational fluid dynamics simulation of a NASA single-stage compressor rotor, which resulted in a reduced model of the simulation (using only three of the five simulation variables) that used only about 4.67% of the full simulation’s storage with an overall average percent error of 8.90%. It was concluded that the NU-DMD, if used appropriately, could be used to possibly reduce a model that uses 400 GB of memory to a model that uses as little as 18.67 GB with less than 9% error. Further conclusions were made about how to best implement the NU-DMD.

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“…For an axial impeller, the hypothesis that stall is initiated by leading edge spillage of ITLMF is supported by many experiments and simulations. 16–19 For a centrifugal impeller, the leading edge spillage of the interface can also be used as a criterion for stall-onset point. 20,21…”

Section: Introductionmentioning

confidence: 99%

One-dimensional modeling for tip clearance leakage vortex trajectory and stall-onset prediction in subsonic centrifugal impellers

Zhang

Dong

Liu

et al. 2019

Proceedings of the Institution of Mechanical Engineers, Part A:

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Two one-dimensional models are established for the tip leakage vortex trajectory and rotating stall-onset point prediction respectively for subsonic centrifugal impellers. The goal of modeling is to supply an effective estimation strategy of the stall-onset point for use in the one-dimensional performance prediction stage. The tip leakage vortex trajectory prediction is a critical part of the stall-onset prediction. The proposed one-dimensional model (one-dimensional tip leakage vortex trajectory model) to predict the tip leakage vortex trajectory is based on blade loading, i.e. the velocity difference between the pressure and suction surfaces. The loading function considers the effect of radial rotation, blade turning, and passage width variation. Compared with the computational fluid dynamics results, the current model shows reasonable accuracy, with an average relative error below 12.35%. The one-dimensional prediction model (Model II) is developed to determine the stall-onset point, where the interface between the tip leakage flow and the main flow spills from the blade leading edge. In this model, the momentum balance analysis is applied to identify the position of the interface. The parameter of the tip leakage vortex trajectory in Model II is determined by one-dimensional tip leakage vortex trajectory model. The effective origin of the tip leakage flow is correlated with the rotational speed and tip clearance. The effectiveness of Model II is validated with the experimental and computational fluid dynamics results using three impellers. Compared with the conventional model (Model I), Model II shows better accuracy, with a maximum error of about 7.42%.

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Prestall Behavior of a Transonic Axial Compressor Stage via Time-Accurate Numerical Simulation

Cited by 14 publications

References 11 publications

Numerical simulation of the non-uniform flow in a full-annulus multi-stage axial compressor with the harmonic balance method

Numerical simulation of the non-uniform flow in a full-annulus multi-stage axial compressor with the harmonic balance method

Using the Nonuniform Dynamic Mode Decomposition to Reduce the Storage Required for PDE Simulations

One-dimensional modeling for tip clearance leakage vortex trajectory and stall-onset prediction in subsonic centrifugal impellers

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