Numerical Simulation of Stall and Stall Control in Axial and Radial Compressors

Chen, Jen‐Ping; Webster, Robert S.; Hathaway, Michael D.; Herrick, Gregory P.; Skoch, Gary J.

doi:10.2514/6.2006-418

Cited by 17 publications

(11 citation statements)

References 18 publications

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“…This boundary condition extrapolates temperature, pressure, and tangential components of velocity to match the compressor exit mass flux corrected to the exit total condition (Ref. 7).…”

Section: Exit Boundary Conditionmentioning

confidence: 99%

Unsteady Full Annulus Simulations of a Transonic Axial Compressor Stage

Herrick

Hathaway

2009

47th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

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“…This boundary condition extrapolates temperature, pressure, and tangential components of velocity to match the compressor exit mass flux corrected to the exit total condition (Ref. 7).…”

Section: Exit Boundary Conditionmentioning

confidence: 99%

Unsteady Full Annulus Simulations of a Transonic Axial Compressor Stage

Herrick

Hathaway

2009

47th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

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“…A highresolution CFD solver, TURBO [10], has recently been proven to be capable of capturing the major characteristics of stall [11]. However, the large size of the simulation results and the lack of visualization tools specific to the problem pose significant challenges for the scientists to study the data.…”

Section: Motivation Background and Approach Overviewmentioning

confidence: 99%

Visualization and Analysis of Rotating Stall for Transonic Jet Engine Simulation

Cher

Dutta

Liu

et al. 2016

IEEE Trans. Visual. Comput. Graphics

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Identification of early signs of rotating stall is essential for the study of turbine engine stability. With recent advancements of high performance computing, high-resolution unsteady flow fields allow in depth exploration of rotating stall and its possible causes. Performing stall analysis, however, involves Significant effort to process large amounts of simulation data, especially when investigating abnormalities across many time steps. In order to assist scientists during the exploration process, we present a visual analytics framework to identify suspected spatiotemporal regions through a comparative visualization so that scientists are able to focus on relevant data in more detail. To achieve this, we propose efficient stall analysis algorithms derived from domain knowledge and convey the analysis results through juxtaposed interactive plots. Using our integrated visualization system, scientists can visually investigate the detected regions for potential stall initiation and further explore these regions to enhance the understanding of this phenomenon. Positive feedback from scientists demonstrate the efficacy of our system in analyzing rotating stall.

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“…However, Reynolds-averaged Navier-Stokes (RANS)-based computational fluid dynamics (CFD) results published in the literature tend to mispredict the performance of centrifugal compressors when compared to available data. [2][3][4][5] In general, the computations tend to over-predict total pressure ratio, efficiency, and in the case of vaned diffuser configurations, the choking flow rate.…”

Section: Introductionmentioning

confidence: 99%

“…An over-prediction in choking flow rate was observed in the CFD result, and this speed line serves to illustrate a trend seen throughout the literature. [2][3][4][5] The CFD results shown are converged, unsteady phaselag computations which were time-averaged over one revolution. Computed static pressures at the exit rating station were area-averaged.…”

Section: Introductionmentioning

confidence: 99%

Computational Study of the CC3 Impeller and Vaneless Diffuser Experiment

Kulkarni

Beach²,

Skoch

2013

49th AIAA/ASME/SAE/ASEE Joint Propulsion Conference

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Centrifugal compressors are compatible with the low exit corrected flows found in the high pressure compressor of turboshaft engines and may play an increasing role in turbofan engines as engine overall pressure ratios increase. Centrifugal compressor stages are difficult to model accurately with RANS CFD solvers. A computational study of the CC3 centrifugal impeller in its vaneless diffuser configuration was undertaken as part of an effort to understand potential causes of RANS CFD mis-prediction in these types of geometries. Three steady, periodic cases of the impeller and diffuser were modeled using the TURBO Parallel Version 4 code: 1) a k-ε turbulence model computation on a 6.8 million point grid using wall functions, 2) a k-ε turbulence model computation on a 14 million point grid integrating to the wall, and 3) a k-ω turbulence model computation on the 14 million point grid integrating to the wall. It was found that all three cases compared favorably to data from inlet to impeller trailing edge, but the k-ε and k-ω computations had disparate results beyond the trailing edge and into the vaneless diffuser. A large region of reversed flow was observed in the k-ε computations which extended from 70% to 100% span at the exit rating plane, whereas the k-ω computation had reversed flow from 95% to 100% span. Compared to experimental data at near-peak-efficiency, the reversed flow region in the k-ε case resulted in an under-prediction in adiabatic efficiency of 8.3 points, whereas the k-ω case was 1.2 points lower in efficiency.

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Numerical Simulation of Stall and Stall Control in Axial and Radial Compressors

Cited by 17 publications

References 18 publications

Unsteady Full Annulus Simulations of a Transonic Axial Compressor Stage

Unsteady Full Annulus Simulations of a Transonic Axial Compressor Stage

Visualization and Analysis of Rotating Stall for Transonic Jet Engine Simulation

Computational Study of the CC3 Impeller and Vaneless Diffuser Experiment

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