CFD Investigations on the Influence of varying Inflow Conditions on the Aerodynamics in an S-Shaped Inlet Duct

Brehm, Sebastian; Kächele, Thomas; Niehuis, Reinhard

doi:10.2514/6.2014-3595

Cited by 6 publications

(3 citation statements)

References 11 publications

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“…Windtunnel investigations were conducted with a scaled model of the intake duct with cropped wings of the forebody. Brehm et al (2014) and Kächele et al (2015a,b) conducted numerical research on double s-shaped intake ducts with varying cross-sectional shapes.…”

Section: Nomenclaturementioning

confidence: 99%

Validation of RANS simulations of the flow in a short highly bent intake duct

Haug¹,

Rademakers²,

Krummenauer³

et al. 2019

European Conference on Turbomachinery Fluid Dynamics and Hermodynamics

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The current development of modern aircraft concepts often focuses on fully integrated propulsion systems. These fully integrated propulsion systems require the use of short highly bent intake ducts. At the Institute of Jet Propulsion a short highly bent intake duct, the Military Engine Intake Research Duct (MEIRD), was designed and developed. The MEIRD was investigated experimentally as well as with steady state RANS simulations with many different numerical setup parameters. From this extensive study, one setup was chosen for detailed investigations. To ensure the validity of the predicted flow phenomena inside the MEIRD, the results were compared with experimental data, gained at the Institute's jet engine test facility. It is shown that good qualitative and quantitative data can be achieved using a proper numerical setup.

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Section: Nomenclaturementioning

confidence: 99%

Validation of RANS simulations of the flow in a short highly bent intake duct

Haug¹,

Rademakers²,

Krummenauer³

et al. 2019

European Conference on Turbomachinery Fluid Dynamics and Hermodynamics

Self Cite

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“…The main reason behind that decision was the absence of similar experimental data referring to this specific airframeengine configuration. CFD technology though has been successfully used elsewhere (11,12) in the simulation of distorted airflow conditions entering intake ducts. The numerical results obtained in these cases were really close to experimental ones which gives confidence, in a roundabout way, to similar suggested methodologies like the one described herein.…”

Section: Effect Of Aoa and Aoss On Maximum Radial Intensitymentioning

confidence: 99%

Total pressure distortion levels at the aerodynamic interface plane of a military aircraft

et al. 2015

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Military aircrafts are often subjected to severe flight maneuvers with high Angles-of -Attack (AOA) and Angles of Sideslip (AOSS). These flight attitudes induce non-uniform in flow conditions to their gas turbine engines which may include distortion of inlet total pressure and total temperature at the Aerodynamic Interface Plane (AIP). Operation of the downstream compression system with distorted inflow typically results in reduced aerodynamic performance, reduced stall margin, and increased blade stress levels. In the present study the steady state total pressure distortion induced to the Aerodynamic Interface Plane due to the aircraft’s flight attitude have been estimated in terms of distortion descriptors. The distorted conditions at the interface between the intake and the engine have been predicted by using Computational Fluid Dynamics (CFD), where 33 different aircraft flight attitudes have been tested. Based on the obtained results the effect of Angle-of-Attack (AOA) and Angle of Side Slip (AOSS) on the distortion descriptors have been studied. The results showed that the distortion effect becomes more pronounced whenever this specific airframe configuration is exposed to incoming flow with an AOSS. Among the tested cases, the greatest total pressure defect at the AIP in terms of difference from the average value and of circumferential extent was calculated for the flight attitudes of 0·35M flight with 0° AOA and 8° AOSS and 0·35M fight with 16° AOA and 16° AOSS.

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“…In Furthermore, many investigators use a KWSST turbulence model for their simulations for not only ow simulation inside the clean S-duct but also for simulations to observe eect of vortex generators, icing and the inow conditions on the ow inside the S-ducts [44,16,59,13].…”

Section: Comments About Validation Studymentioning

confidence: 99%

Passive Flow Control in Boundary Layer Ingesting Semi Submerged Inlet

Küçük¹,

Baran²,

Uzol³

2015

51st AIAA/SAE/ASEE Joint Propulsion Conference

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Submerged intake designs with high compactness provide lower radar cross sectional area, less noise, higher packaging eciency and lower drag compared to the conventional designs. However, in such an intake ow exposed to strong adverse pressure gradients both in streamwise and circumferential directions due to the centerline curvature and high diusion rate through the intake. Since, ow inside submerged intakes is very sensitive to the upcoming ow quality, it is very common to encounter with high total pressure distortion and low total pressure recovery inside boundary layer ingesting submerged intakes. Therefore, ow control methods used for reducing distortion and/or increasing pressure recovery can provide crucial advantageous to the intake designers. In this thesis, eect of vortex generators used as a passive ow control devices in a semi submerged boundary layer ingesting intake is computationally investigated with commercially available ow solver Fluent 14.0. In order to reach high condence about v computational strategy and turbulence model selection validation study is conducted with an available experimental data in the open literature for a serpentine intake with and without vortex generator application. Validation results indicate that κ − ω SST provide more accurate results compared to the computations obtained with Spalart Allmaras and Realizable κ − ε turbulence models. Base intake geometry developed for a ow control investigation is formed through the conventional design approaches. After computational investigation of performance of clean intake without ow control, eect of vortex generators on intake performance are investigated. Design variables of vortex generator sets are taken as vortex generator height relative to local boundary layer thickness, angle of incidence, number of vortex generators thus lateral spacing and distance between separation point and vortex generator set. Eect of the each design variable on intake performance are discussed in detail at the end of the work. Best vortex generator set provide 80% reduction in total pressure distortion with only 0.35% reduction in total pressure recovery at design condition. Moreover it is shown that, passive ow control ensure suciently uniform ow reaching engine face such that possibility of the engine surge totally eliminated with only negligible decrease in pressure recovery for not only design condition but also whole angle of attack range that mostly encountered in ight envelope.

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CFD Investigations on the Influence of varying Inflow Conditions on the Aerodynamics in an S-Shaped Inlet Duct

Cited by 6 publications

References 11 publications

Validation of RANS simulations of the flow in a short highly bent intake duct

Validation of RANS simulations of the flow in a short highly bent intake duct

Total pressure distortion levels at the aerodynamic interface plane of a military aircraft

Passive Flow Control in Boundary Layer Ingesting Semi Submerged Inlet

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