A Computational Investigation of Icing Effects on an S-Duct Inlet

Jin, Wonjin; Taghavi, Ray; Farokhi, Saeed

doi:10.1515/tjj.2010.27.3-4.277

Cited by 3 publications

(3 citation statements)

References 1 publication

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“…The upstream extension is placed to develop boundary layer and the downstream extension is mounted in order to push back the computational domain with respect to engine face. These extensions were also used in the earlier studies [44] and [28]. Duct geometry modeled as ow domain is shown in the gure 3.21.…”

Section: Computational Domain and Duct Geometrymentioning

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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Section: Computational Domain and Duct Geometrymentioning

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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“…found to create higher performance degradation due to its horn shape, according to Jin and Taghavi (14) . As a result, in the present study, the effect of glaze ice accretion on the steady-state flowfield inside the M2129 inlet is computationally investigated at freestream Mach numbers of 0 .…”

Section: Inlet Icingmentioning

confidence: 99%

Flow distortion in an S-duct inlet with simulated icing effect and heat transfer

Jin

Taghav

Farokhi

2012

Aeronaut. j. (1968)

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A diffusing S-duct aircraft intake system is computationally studied for the effects of inlet icing and wall heat transfer on engine face distortion. A Reynolds-Averaged Navier-Stokes (RANS) code with k-ω SST turbulence model is used to simulate the compressible viscous flow in the duct. The glaze ice accretion on the inlet lip is simulated as a fixed protrusion from NASA LEWICE3D code. The shape and size of the ice on the inlet lip are assumed to remain constant even in the case of the heated wall. The case of zero external heat transfer is modeled by the adiabatic wall boundary condition, and constant-wall temperature is used to simulate the heated wall effect. The freestream Mach number of 0 . 85 and glaze ice condition on the inlet lip produce massive flow separation at the lip and internal shock cell structure in the S-duct. The heated wall creates additional vorticity and thus increases the engine face distortion level. The areaaveraged total pressure distortion at the engine face in a freestream Mach number of 0 . 85 is increased by ~7% in the heated wall case as compared to the adiabatic flow. NOMENCLATURE DCtotal pressure distortion coefficient, defined in Equation (5) DP total pressure distortion parameter, defined in Equation (4) LWC liquid water content, g/m 3

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“…또한 엔진 공기흡입구 주변에 형성된 결빙은 공기의 흐름을 교란시켜 전압력 회복율 감소 및 왜곡율 증가 등 엔진 성 능을 저하시키고, 흡입구 주위에서 박리된 얼음 조각이 엔진에 유입되면 압축기나 팬이 손상되어 극한의 경우 엔진 기능이 정지될 수 있다 (2) . 결빙 관련 연구는 1930년대에 그 중요성이 부 각되어 시작되었으며, 현 결빙연구의 기초가 되 는 결빙에 의한 공력 영향성 분석은 풍동시험과 비행시험을 바탕으로 1950년대에 이루어졌다.…”

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Investigation of the Performance of Anti-Icing System of a Rotorcraft Engine Air Intake

Ahn¹,

Jung²,

Jung³

et al. 2013

Journal of the Korean Society for Aeronautical & Space Scie

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Ice accretions on the surface around a rotorcraft air intake can deteriorate the safety of rotorcraft due to the engine performance degradation. The computational simulation based on modern CFD methods can be considered extremely valuable in analyzing icing effects before exact but very expensive icing wind tunnel or in-flight tests are conducted. In this study the range and amount of ice on the surface of anti-icing equipment are investigated for heat-on and heat-off modes. It is demonstrated through the computational prediction and the icing wind tunnel test that the maximum mass and height of ice of heat-on mode are reduced about 80% in comparison with those of heat-off mode.

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A Computational Investigation of Icing Effects on an S-Duct Inlet

Abstract: The effects of a typical glaze ice accretion shape on the performance of the M2129 S-duct inlet are computationally

Cited by 3 publications

References 1 publication

Passive Flow Control in Boundary Layer Ingesting Semi Submerged Inlet

Passive Flow Control in Boundary Layer Ingesting Semi Submerged Inlet

Flow distortion in an S-duct inlet with simulated icing effect and heat transfer

Investigation of the Performance of Anti-Icing System of a Rotorcraft Engine Air Intake

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