Computational Study of the Effects of Ice Accretions on the Flowfields in the M2129 S Duct inlets

Jin, Wonjin; Taghavi, Ray

doi:10.2514/6.2008-75

Cited by 4 publications

(3 citation statements)

References 7 publications

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“…Once the ice becomes thicker and thicker, the mass flow rate of airflow would reduce, that would lead to engine performance deterioration. If the ice accretes severely, the engine couldn't work normally and even endanger the aircraft [1,2]. It is one of the main hazards to flying.…”

Section: Introductionmentioning

confidence: 99%

Research on Numerical Simulation of Three-dimensional Icing for Aircraft and Aero-engine

Li¹,

HU²

2018

dtmse

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Based on the idea of modularization, the three-dimensional icing calculation research code for aircraft and aero-engine is developed by using the secondary development features (UDF) of FLUENT. By analyzing the physical process of aircraft and engine inlet parts icing, two-phase flow field calculation, water droplets collect calculation, thermodynamic calculation of icing, wall mesh calculation program is compiled, four calculation modules of icing calculation program were realized. By solving the key problem of data exchange and control solution process between the secondary development program and the four calculation modules, the module integration is completed and the three-dimensional icing numerical simulation of icing components of aircraft and aero-engine was realized. The calculation of icing on NACA0012 3D airfoil is carried out, and compared with the experimental results in literature. The results show that the maximum icing thickness is in good agreement with the experimental results, and the predicted ice shape is consistent with the experimental ice shape development trend. The calculation results show that the proposed three-dimensional icing calculation method is effective and reliable. On the basis of this, numerical simulation of icing was carried out on the trailing adjusted strut of aero-engine inlet with a tail angle of 0 °, and the water collection coefficient of the strut wall and the icing area of the strut at different time were obtained. It provides a new method for pre-researching aircraft and aero-engine icing.

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Section: Introductionmentioning

confidence: 99%

Research on Numerical Simulation of Three-dimensional Icing for Aircraft and Aero-engine

Li¹,

HU²

2018

dtmse

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“…While there are many researches done on the effects of icing on wings and airfoils, however, relatively less attention has been paid to the icing effects on the performance of engine inlets, although the effects can be hazardous to engines and aircraft. In particular, ice accretion on the aircraft engine inlet lip can alter the shape of the inlet lip and can cause serious degradation of the performance of an engine inlet (Jin and Taghavi 2008).…”

Section: Introductionmentioning

confidence: 99%

Experimental Investigation on the Ice Accretion Effects of Airplane Compressor Cascade of Stator Blades on the Aerodynamic Coefficients

Ramezanizadeh¹,

S.M.H.²,

Mirzaei

et al. 2013

JAFM

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In this paper the effects of ice accretion on the pressure distribution and the aerodynamic coefficients in a cascade of stator blades were experimentally investigated. Experiments were conducted on stage 67A type stator Controlled-Diffusion blades, which represent the mid-span of the first stage of the stator for a high-bypass turbofan engine. The measurements were carried out over a range of cascade angle of attack from 20° to 45° at Reynolds number of 500000. Experimental blade surface pressure coefficient distribution, lift and drag force coefficients, and momentum coefficients for clean blades were compared with those of the iced blades and the effects of ice accretion on these parameters were discussed. It is observed that the ice accretion on the blades causes the formation of flow bubble on the pressure side, downstream of the leading edge. By increasing the angle of attack from 20° to 35°, the bubble length decreases and the pressure coefficient increases inside the bubble region, constantly. In addition, for the iced blades the diffusion points at the suction side come closer to the trailing edge. In addition, it is found that by increasing the angle of attack up to 35°, the ice accretion has no significant effect on the lift coefficient but the drag coefficient increases comparing with the clean blades. More over at 40° and 45°, by increasing the flow interference effects between the blades, the iced blades experience higher lift and lower drag in comparison with the clean ones.

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“…In their work, the shapes of a typical rime and glaze ice on the axisymmetrical inlet lip were numerically defined in the icing conditions;˛DˇD , T s1 D 9:3 ı C (263.9 K), icing time D 30 minutes for rime and glaze, respectively. Also, the effects of the Bidwell's rime and glaze ice shape on the performance of the M2129 diffusing S-duct inlet were computationally investigated by Jin and Taghavi ( [11]). In their investigation, the (area-averaged) total pressure recovery of the M2129 inlet decreased by 3.2 percent at M 1 D 0:23 when the glaze ice was simulated on the inlet lip in the case of zero angle of attack, while only 0.2 percent-reduction occurred with the rime ice shape.…”

Section: Greek Symbolsmentioning

confidence: 99%

Asymmetrical Flow Simulation of Icing Effects in S-Duct Inlets at Angle of Attack

Jin¹,

Taghavi²,

Farokhi

2011

International Journal of Turbo and Jet Engines

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Abstract. The effect of flow angularity on an S-duct inlet with icing is computationally investigated. Flow angularity is simulated through angle-of-attack, and sideslip in addition to asymmetrical ice accretion on the inlet lip. A commercial CFD code, STAR-CCM+ is used for the steadystate computations with the shear-stress transport (SST) k-! turbulence model. Symmetrical and asymmetrical glaze ice shapes are computationally simulated on the inlet lip. The symmetrical glaze ice uniformly covers the entire cowl lip; whereas the asymmetrical glaze ice is simulated on a 1=4 sector of the inlet lip and is positioned on top, bottom or side of the inlet lip. The results indicate that flow angularity, whether in angle-of-attack or sideslip, aggravates the low performance of inlets with icing. The total pressure recovery suffers an additional 2% loss and the inlet mass flow rate drops by 7% when the inlet is at C20 ı angle of attack, as compared to zero angle, for flight Mach number of 0.34. The extent of loss in total pressure and a drop in mass flow rate depends on the asymmetrical icing location as well as the inlet angle-of-attack and sideslip. In addition, the ice-induced flow blockage is identified as a critical inlet performance parameter, since the symmetrical (360 ı ) glaze ice with its wider flow blockage creates a lower total pressure recovery than the asymmetrical (90 ı ) glaze ice at all angles of attack or sideslip.

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Computational Study of the Effects of Ice Accretions on the Flowfields in the M2129 S Duct inlets

Cited by 4 publications

References 7 publications

Research on Numerical Simulation of Three-dimensional Icing for Aircraft and Aero-engine

Research on Numerical Simulation of Three-dimensional Icing for Aircraft and Aero-engine

Experimental Investigation on the Ice Accretion Effects of Airplane Compressor Cascade of Stator Blades on the Aerodynamic Coefficients

Asymmetrical Flow Simulation of Icing Effects in S-Duct Inlets at Angle of Attack

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