CFD Performance Predictions of a Serpentine Diffuser Configuration in an Annular Cascade Facility

Sanders, Darius; List, Michael G.; Nessler, Chase; Copenhaver, William W.

doi:10.2514/6.2013-220

Cited by 6 publications

(6 citation statements)

References 8 publications

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“…This deficit at the AIP is seen in similar investigations of typical S-ducts and has been shown to be a function of a counter-rotating vortical structure [3,[6][7][8][9]. The parallel computational effort performed by Sanders et al [16], shows this top pressure deficit is in fact due to a pair of counter-rotating vortices that formed from the upper surface just downstream of the separation. In addition to this, there were three other localized pressure deficits visible at the AIP.…”

Section: Figure 15 Circumferential Static Pressure Distribution At Tsupporting

confidence: 52%

“…The presence of this gradient gives an indication that secondary flow is present within the flow field. The extent of the secondary flow was not measured in the current investigation, but was shown to exist in the corresponding computational efforts [15][16]. The effect of this secondary flow is apparent in the AIP total pressure profiles shown below.…”

Section: Figure 15 Circumferential Static Pressure Distribution At Tmentioning

confidence: 93%

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Serpentine Diffuser Performance with Emphasis on Future Introduction to a Transonic Fan

Nessler

Copenhaver

List

2013

51st AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

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Section: Figure 15 Circumferential Static Pressure Distribution At Tsupporting

confidence: 52%

Section: Figure 15 Circumferential Static Pressure Distribution At Tmentioning

confidence: 93%

Serpentine Diffuser Performance with Emphasis on Future Introduction to a Transonic Fan

Nessler

Copenhaver

List

2013

51st AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

Self Cite

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“…Returning to the internal flow field, another important characteristic of S-duct flows is the presence of a loss in total pressure due to separation inside of the duct, particularly that from the second turn, as noted by Wellborn et al [32], Nessler et al [33], and Sanders and List [34], for example. Total pressure was calculated using equation (8), which is identical to equation ( 5), but solved for total pressure.…”

Section: Streamwise Vorticitymentioning

confidence: 96%

Geometric scattering removal in cross-correlation Doppler global velocimetry by structured illumination

Boyda¹,

Byun²,

Saltzman³

et al. 2020

Meas. Sci. Technol.

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The biases introduced by background light contributions in planar, Doppler-based velocimetry are significantly reduced by the application of structured illumination. The method works by measuring and separating desired flow-scattered signals from unwanted reflections and secondary scattering contributions via a sinusoidal intensity modulation across the laser sheet used to interrogate the flow. In the current work we consider the influence of background light on cross-correlation Doppler global velocimetry (CC-DGV) and present the results for measurements in a turbulent free jet with an exit Mach number of 0.5 in a measurement arrangement with high intensity background contributions. It is shown that if the ratio of the particle-scattering (i.e. Mie scattering) intensity to the background solid surface scattering (i.e. geometric scattering) intensity is greater than 10, then the measured signal displays a significant bias away from the true velocity. With structured illumination, the measured intensity corresponding to geometric scattering is reduced to negligible levels, reminiscent of a measurement arrangement with little or no background light influence. Centreline velocity measurements with this background subtraction method are compared with Kiel-type pressure probe measurements, yielding a root-mean-square (RMS) difference between the two of 1.2 m s -1 (less than 1% of the full scale velocity), well within the published uncertainty bound of the CC-DGV technique, underscoring the robustness of this approach. In addition to the centreline validation, the streamwise vorticity and total pressure are also analysed, showing trends indicative of the S-type shape of the duct and aggressive flow entrainment experienced in this environment.

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“…[10] discussed the experimental and numerical quantification of distortion generation through an aggressive diffuser. Circumferential distributions of total pressure, total temperature, static pressure and static temperature were measured experimentally at multiple axial locations.…”

mentioning

confidence: 99%

“…discusses best practices for turbomachinery meshes in STAR-CCM+, as well as the mesh generation process and troubleshooting of errors in the mesh. The best practices discussed are taken from a combination of the STAR-CCM+ manual, turbomachinery specialists at CD-Adapco and Nessler and Sanders[9] [10]. Although the recommendations and best practices outlined in this section are intended for STAR-CCM+, many of the principles can be applied to any turbomachinery CFD mesh.…”

mentioning

confidence: 99%

Implementation of Fourier methods in CFD to analyze distortion transfer and generation through a transonic fan

Peterson¹,

Gorrell²,

List³

et al. 2016

52nd AIAA/SAE/ASEE Joint Propulsion Conference

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Inlet flow distortion is a non-uniform total pressure, total temperature, or swirl (flow angularity) condition at an aircraft engine inlet. Inlet distortion is a critical consideration in modern fan and compressor design. This is especially true as the industry continues to increase the efficiency and operating range of air breathing gas turbine engines. The focus of this paper is to evaluate the Computational Fluid Dynamics (CFD) Harmonic Balance (HB) solver in STAR-CCM+ as a reduced order method for capturing inlet distortion as well as the associated distortion transfer and generation. New methods for quantitatively describing and analyzing distortion transfer and generation are investigated. The geometry used is the rotor 4 fan geometry, consisting of one rotor and one stator. The inlet boundary condition is a 90 • sector total pressure distortion profile with total pressure and swirl held constant. Multiple HB simulations with varying mode combinations and distortion intensities are analyzed and compared against full annulus Unsteady Reynolds Averaged Navier-Stokes (URANS) simulations. Best practices and recommendations for the implementation of the HB solver are given. The pre-existing Society of Automotive Engineers Aerospace Recommended Practice (SAE-ARP) 1420b descriptors are demonstrated to be inadequate for the purposes of analyzing distortion transfer and generation on a stage-to-stage basis. New implementations of Fourier methods are presented as an alternative to the SAE-ARP 1420b descriptors. These Fourier descriptors are shown to describe distortion transfer and generation to a higher degree of fidelity than the SAE-ARP 1420b descriptors. These new descriptors are demonstrated on the analysis of full annulus URANS and HB simulations. The HB solver is shown to be capable of capturing distortion transfer, generation and performance degradation. Recommendations for the optimal implementation of the HB method are given.

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CFD Performance Predictions of a Serpentine Diffuser Configuration in an Annular Cascade Facility

Cited by 6 publications

References 8 publications

Serpentine Diffuser Performance with Emphasis on Future Introduction to a Transonic Fan

Serpentine Diffuser Performance with Emphasis on Future Introduction to a Transonic Fan

Geometric scattering removal in cross-correlation Doppler global velocimetry by structured illumination

Implementation of Fourier methods in CFD to analyze distortion transfer and generation through a transonic fan

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