Ice Accretion Measurements on an Airfoil and Wedge in Mixed-Phase Conditions

Struk, Peter M.; Bartkus, Tadas P.; Tsao, Jen-Ching; Currie, Thomas E.; Fuleki, Dan

doi:10.4271/2015-01-2116

Cited by 30 publications

(20 citation statements)

References 10 publications

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“…In 2012, Struk et al [11] used both a wedge aerofoil and a NACA 0012 aerofoil in RATFac to investigate accretion growth rate as a function of flow velocity and wet bulb temperature. At a velocity of approximately 85 m/s, a peak growth rate was found for melt ratios in the region 6 -12 %.…”

Section: Introductionmentioning

confidence: 99%

Experimental Studies of Ice Crystal Accretion on an Axisymmetric Body at Engine-Realistic Conditions

Bucknell

McGilvray

Gillespie

et al. 2018

2018 Atmospheric and Space Environments Conference

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Section: Introductionmentioning

confidence: 99%

Experimental Studies of Ice Crystal Accretion on an Axisymmetric Body at Engine-Realistic Conditions

Bucknell

McGilvray

Gillespie

et al. 2018

2018 Atmospheric and Space Environments Conference

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“…where , the velocity, is taken as the accretion growth rate ℎ̇. Using typical value from previous experiments in crystal test facilities results in ≅ 0.5 [16]. This shows that the validity of the assumption in ice crystal icing conditions is marginalcompared to supercooled water icing where the growth rate, ℎ̇, is typically significantly lower [10].…”

Section: Model Assumptionsmentioning

confidence: 79%

A Three-Layer Thermodynamic Model for Ice Crystal Accretion on Warm Surfaces: EMM-C

Bucknell¹,

McGilvray²,

Gillespie³

et al. 2019

SAE Technical Paper Series

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Ingestion of high altitude atmospheric ice particles can be hazardous to gas turbine engines in flight. Ice accretion may occur in the core compression system, leading to blockage of the core gas path, blade damage and/or flameout. Numerous engine powerloss events since 1990 have been attributed to this mechanism. An expansion in engine certification requirements to incorporate ice crystal conditions has spurred efforts to develop analytical models for phenomenon, as a method of demonstrating safe operation. A necessary component of a complete analytical icing model is a thermodynamic accretion model. Continuity and energy balances are performed using the local flow conditions and the mass fluxes of ice and water that are incident on a surface to predict the accretion growth rate. In this paper, a new thermodynamic model for ice crystal accretion is developed through adaptation of the Extended Messinger Model (EMM) from supercooled water conditions to mixed phase conditions (ice crystal and supercooled water). A novel three-layer accretion structure is proposed and the underlying equations described. The EMM improves upon the original model for airframe icing, the Messinger Model, by permitting a linear temperature gradient through the ice and water layers. This in turn allows prediction of the time over which water exists in isolation on an initially warm surface, before an ice layer forms. This is of particular interest to engine icing, as surfaces may initially be significantly above freezing temperature, before cooling on exposure to ice particles. The method is solved in a multi-step approach, where the overall exposure time is divided into discrete windows, and the calculation performed over each window. This allows the local flow conditions to be updated between windows, permitting the incorporation of a reducing flow enthalpy due to particle evaporation, as well as transient engine operation. Model results are then compared to experimental results. Comparisons are made to solutions generated using the standard Messinger Model.

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“…A key goal of the NASA Engine Icing Research is to better understand the complex physics and possible interaction of the icecrystal icing (ICI) phenomena that take place inside a modern turbofan engine in order to develop numerical simulation models of various fidelity, with the goal to determine possible engine icing onset conditions and locations; predict ice accretion locations, profiles and sizes; and evaluate/address design challenges to mitigate the risks [1]. The NASA Engine Icing Research team has continued developing its understanding of ice-crystal icing through a number of full scale engine test campaigns conducted in the PSL [2][3][4][5][6][7] and a series of fundamental ICI physics experimental studies conducted on a NACA 0012 airfoil in the NRC Research Altitude Test Facility (RATFac) and the NASA Propulsion Systems Laboratory (PSL) [8][9][10][11][12][13]. A simulated altitude engine icing test facility like the PSL enables highly controlled environmental simulations at relevant flight conditions to be examined.…”

Section: Introductionmentioning

confidence: 99%

Scaling Evaluation of Ice-Crystal Icing on a Modern Turbofan Engine in PSL Using the COMDES-MELT Code

Tsao

2019

SAE Technical Paper Series

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This paper presents preliminary ice-crystal icing (ICI) altitude scaling evaluation results of a Honeywell Uncertified Research Engine (HURE) that was tested in the NASA Glenn Research Center Propulsion Systems Laboratory (PSL) during January of 2018. This engine geometry features a hidden core design to keep the core less exposed. The engine was fitted with internal video cameras to observe various ice buildup processes at multiple selected locations within the engine core flow path covering the fan stator, the splitterlip/shroud/strut, and the high pressure compressor (HPC) variable inlet guide vane (IGV) regions. The potential ice accretion risk was predetermined to occur by using NASA's in-house 1D Engine Icing Risk assessment code, COMDES-MELT. The code was successful in predicting the risk of ice accretion in adiabatic regions like the fanstator of the HURE at specific engine operating points. However at several operating points during the test, liquid water was observed running along the shroud toward the variable IGV of the HPC regions with an air temperature well below freezing, thus no particle melting could have occurred due to heating from the air alone. It was reasoned that other sources of heat were present in that region. To account for these heat sources the inlet total temperature was adjusted to give a wet bulb temperature of 24 F below the standard minimum wet bulb temperature of 492 R to allow ice to accrete in the splitterlip/shroud/strut region, which was determined from a reference case where hard ice was observed in that region. With that adjustment the COMDES-MELT code was successful in providing operating points where there was a risk of ice accretion during the test campaign. In addition to calculating possible conditions at different selected lower altitudes, simulations were run to determine potential inlet conditions that could lead to ice-crystal accretion along the prescribed stations where the cameras were available. From there, scaled test conditions were determined by best matching the following three icing related parameters of the reference condition: (1) the local air total wet bulb temperature, (2) the local ice crystal cloud melt ratio and (3) the engine fan face ice/water to air mass flux ratio of the ice crystal cloud. Instantaneous images taken from the time-lapsed movies of ice buildup were used along with the relevant thermodynamic data of air, water vapor and local icing condition to help evaluate how closely the proposed altitude scaling method could be used in ground based test facility to duplicate selected reference ICI features observed at specific location inside this engine at different scale altitudes. Discussions on observed limitation for engine icing scaling application from this test campaign and needed improvement are provided. A scaling test procedure to help identify potential ICI risk conditions and possible ice accretion locations of a new turbofan engine is evaluated in PSL.

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Ice Accretion Measurements on an Airfoil and Wedge in Mixed-Phase Conditions

Cited by 30 publications

References 10 publications

Experimental Studies of Ice Crystal Accretion on an Axisymmetric Body at Engine-Realistic Conditions

Experimental Studies of Ice Crystal Accretion on an Axisymmetric Body at Engine-Realistic Conditions

A Three-Layer Thermodynamic Model for Ice Crystal Accretion on Warm Surfaces: EMM-C

Scaling Evaluation of Ice-Crystal Icing on a Modern Turbofan Engine in PSL Using the COMDES-MELT Code

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