Study on the aerodynamic performance of boundary-layer-ingesting inlet with various geometries

Li, Zhiping; Zhang, Yafei; Pan, Tianyu; Zhang, Jian; Shang, Yinhui

doi:10.1177/09544100211007386

Cited by 4 publications

(2 citation statements)

References 34 publications

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“…Rein and Koch 48 demonstrated that the distortion at the AIP increases proportionally with the thickness of the inlet boundary layer. Thick boundary layers were found to reduce also the pressure recovery on the intake [49][50][51] and to promote non-uniform radial pressure loading on the compressor blades which could trigger stall inception. 4 Different azimuthal orientations of the approaching boundary layer were also investigated for intakes under yaw and pitch angles 52,53,18 were found to notably influence the fan-face pressure and swirl distortion.…”

Section: Introductionmentioning

confidence: 99%

“…However, the associated peak distortion levels were not assessed as a part of these previous studies and most studies were limited to investigations on the time-averaged components. 50 The understanding of peak distortion levels is a key aspect for the evaluation of the engine response to the inlet distortion. Indeed, it is believed that peak fluctuations of pressure, vorticity and velocity can all play a role in the spike-type stall inception mechanism, which is a source of instability for modern, highly loaded compressors.…”

Section: Introductionmentioning

confidence: 99%

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S-duct flow distortion with non-uniform inlet conditions

Migliorini

Zachos

MacManus

et al. 2022

Proceedings of the Institution of Mechanical Engineers, Part G:

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Convoluted aero-engine intakes are often required to enable closer integration between engine and airframe. Although the majority of previous research focused on the distortion of S-duct intakes with undistorted inlet conditions, there is a need to investigate the impact of more challenging inlet conditions at which the intake duct is expected to operate. The impact of inlet vortices and total pressure profiles on the inherent unsteady flow distortion of an S-duct intake was assessed with stereo particle image velocimetry. Inlet vortices disrupted the characteristic flow switching mode but had a modest impact on the peak levels and unsteady fluctuations. Non-uniform inlet total pressure profiles increased the peak swirl intensity and its unsteadiness. The frequency of swirl angle fluctuations was sensitive to the azimuthal orientation of the non-uniform total pressure distribution. The modelling of peak distortion with the extreme value theory revealed that although for some inlet configurations the measured peak swirl intensity was similar, the growth rate of the peak values beyond the experimental observations was substantially different and it was related with the measured flow unsteadiness. This highlights the need of unsteady swirl distortion measurements and the use of statistical models to assess the time-invariant peak distortion levels. Overall, the work shows it is vital to include the effect of the inlet flow conditions as it substantially alters the characteristics of the complex intake flow distortion.

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Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

S-duct flow distortion with non-uniform inlet conditions

Migliorini

Zachos

MacManus

et al. 2022

Proceedings of the Institution of Mechanical Engineers, Part G:

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Adjoint based aerodynamic shape optimization of a semi-submerged inlet duct and upstream inlet surface

Küçük,

Tuncer

2024

Optim Eng

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Design Optimization of a Novel Flush Boundary Layer Diverter

Küçük,

Tuncer

2024

Journal of Turbomachinery

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A novel boundary layer diverter is designed and optimized for increasing the performance of a typical semi- submerged inlet ingesting large amounts of boundary layer flow. A conceptual diverter configuration based on the prior optimization study is first parametrized with 7 design variables. A response surface model is constructed for the pressure recovery at the AIP. The flow fields over the diverter and through the inlet duct are computed with SU2 and a baseline diverter is constructed from the response surface model for maximum pressure recovery. The baseline diverter is then placed in a free-form deformation box and shape-optimized using the adjoint solver of SU2 with hundreds of design parameters. The optimum configuration provides 2.4% and 7.93% increase in the pressure recovery and the mass flow rate, respectively together with a significant reduction in flow distortion. The novel diverter is then shape-optimized together with the inlet duct. Together with all the performance parameters the pressure recovery is improved by more than 3%. It is shown that the novel boundary layer diverter by being flush to the inlet surface induces a much smaller drag compared to the conventional diverters.

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Study on the aerodynamic performance of boundary-layer-ingesting inlet with various geometries

Cited by 4 publications

References 34 publications

S-duct flow distortion with non-uniform inlet conditions

S-duct flow distortion with non-uniform inlet conditions

Adjoint based aerodynamic shape optimization of a semi-submerged inlet duct and upstream inlet surface

Design Optimization of a Novel Flush Boundary Layer Diverter

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