Development of a Coupled Air and Particle Thermal Model for Engine Icing Test Facilities

Bartkus, Tadas P.; Struk, Peter M.; Tsao, Jen-Ching

doi:10.4271/2015-01-2155

Cited by 28 publications

(24 citation statements)

References 17 publications

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“…An interesting observation, consistent with previous tests, is that the wet-bulb temperature change is small when comparing cloud-off to cloud-on conditions. The interested reader is directed to Bartkus et al [9][10][11] for some modelling work which further discusses the coupling of the cloud with the thermal conditions of the flow.…”

Section: A Humidity (Twb) Sweep Resultsmentioning

confidence: 99%

“…The most recent joint NASA and NRC test 7 in March 2012 included a traversable total air temperature (TAT) & relative humidity (RH) probe 8 which allowed measurements at tunnel centerline. Subsequent modelling showed that a decreasing air temperature was due to the energy exchange from the partial evaporation of the cloud [9][10][11] . The temperature change was sometimes as much as several degrees Celsius, which is significant for icing tests, and measurements of the cloud-on conditions are continued to the present testing.…”

Section: Introductionmentioning

confidence: 99%

“…* The specific cases targeted to be replicated in this work were scans 1123, 1139, 1286 from Currie et al11 …”

mentioning

confidence: 99%

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Ice Crystal Icing Physics Study using a NACA 0012 Airfoil at the National Research Council of Canada’s Research Altitude Test Facility

Struk

King

Bartkus

et al. 2018

2018 Atmospheric and Space Environments Conference

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This paper presents results from a study of the fundamental physics of ice-crystal ice accretion using a NACA 0012 airfoil at the National Research Council of Canada (NRC) Research Altitude Test Facility in August 2017. These tests were a continuation of work which began in 2010 as part of a joint collaboration between NASA and NRC. The research seeks to generate icing conditions representative of those that occur inside a jet engine when ingesting ice crystals. In this test, an airfoil was exposed to mixed-phase icing conditions and the resulting ice accretions were recorded and analyzed. This paper details the specific objectives, procedures, and measurements which included the aero-thermal and cloud measurements. The objectives were built upon observations and hypothesis generated from several previous test campaigns regarding mixed-phase ice-crystal icing. The specific objectives included (A) ice accretions under different wet-bulb temperatures, (B) investigations of steady-state ice shapes previously reported in the literature, (C) total water content variations in search of a threshold for accretion, and (D) probe characterization related to measuring melt fraction which is important to characterize the mixed-phase condition. The resulting ice accretions and conditions leading to such accretions are intended to help extend NASA's predictive iceaccretion codes to include conditions occurring in engine ice-crystal icing.

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Section: A Humidity (Twb) Sweep Resultsmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Ice Crystal Icing Physics Study using a NACA 0012 Airfoil at the National Research Council of Canada’s Research Altitude Test Facility

Struk

King

Bartkus

et al. 2018

2018 Atmospheric and Space Environments Conference

Self Cite

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“…An analytical thermal model was initially developed (Ref. [9]) to explain the observed changes in test conditions by coupling the conservation of mass and energy equations between the icing cloud and flowing air. The model will be referred to as the Bartkus thermal model.…”

Section: Thermal Modelmentioning

confidence: 99%

“…The large temperature difference, or gradient, between the water droplet and the airflow drives the convective heat transfer between droplet and the air. More details on these interactions and thermal mechanisms are provided in Ref [9].…”

Section: Thermal Modelmentioning

confidence: 99%

Total Temperature Measurements Using a Rearward Facing Probe in Supercool Liquid Droplet and Ice Crystal Clouds

Agui

Struk

Bartkus

2018

2018 Atmospheric and Space Environments Conference

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This paper presents an analysis of local total temperature and humidity experimental measurement taken in atmospheric ice cloud flows. The measurements were obtained in a series of tests in NASA's Propulsion Systems Laboratory. The probe used in the tests is referred to as the Rearward Facing Probe which was designed to mitigate the contamination effects of ice accretion and ingestion into the probe. The data provided important insights in the interaction of the ice cloud and the atmospheric flow. For the majority of the test runs, small temperature drops in the range of 0.6 to 2.8 ⁰C and up to 1.5 g/kg of water vapor rise were found as a result of the interaction. Under certain very low temperature or high TWC conditions, the interaction with the cloud produced a warming of the airflow. A thermal model based on evaporative and convective heat transfer mechanisms between the spray droplets and the airflow showed good agreement with the experimental data. Detailed analyses of the response of the probe under various flow, thermodynamic, and cloud conditions, are provided in the paper.

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Kinetic and thermal simulation of water droplets in icing wind tunnels

et al. 2021

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Within the certification process of aircraft, tests under specific icing conditions are required. For such safety relevant tests—which are performed under defined and repeatable test conditions—specially equipped Icing Wind Tunnels (IWT) are required. In such IWTs, supercooled water droplets are created with the aid of a spray system injecting pre-tempered water droplets of specific diameters into the free stream air flow. Especially tests with a droplet size up to 2mm (Supercooled Large Droplets - SLDs) are of great importance. SLDs are difficult to generate under laboratory conditions in IWT since usually the available droplet flight time from the injection location to the impact position on the test object is insufficient to reliably cool down a droplet at least to freezing temperature. To investigate the limitations associated with the application of SLD, the current work provides a method to allow detailed insight into the behavior of droplets on the path from the injection spray nozzle to the test section. In this work a state space model of a single droplet is derived that combines the kinetic aspects, thermal properties as well as the governing differential equations for motion, convective heat transfer at the droplet surface and heat conduction inside the droplet. Beside the states for the droplet’s position and velocity in space, the state space vector comprises various fluid and thermodynamic parameters. The droplet-internal temperature distribution is modelled by a discrete one-dimensional spherical shell model that also incorporates the aggregate phase (freezing mass fraction) at each shell node. This approach allows, therefore, the simulation of potential droplet phase change processes (freezing/melting) as well. With the model at hand, the influence of various boundary conditions (initial droplet temperature, flow field, ambient air temperature, etc.) can be determined and evaluated. As a result, concrete measures to achieve a desired operating condition (e.g. droplet temperature at the test object) for various model assumptions can be derived. In addition, the simulation model facilitates the prediction of the droplet diameter threshold for ensuring a supercooled state upon the impact on the test object. The governing theoretical influences are described, and various simulation results for representative test conditions that occur at the Rail-Tec-Arsenal (RTA) in Vienna are presented.

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Development of a Coupled Air and Particle Thermal Model for Engine Icing Test Facilities

Abstract: Air Control Volume Particle Control Volumes Air Control Volume Particle Control Volumes Fundamental Control Volume UnitSingle particle depiction (uniform particle size cloud) Full particle size distribution particle depiction (multiple particle size cloud)

Cited by 28 publications

References 17 publications

Ice Crystal Icing Physics Study using a NACA 0012 Airfoil at the National Research Council of Canada’s Research Altitude Test Facility

Ice Crystal Icing Physics Study using a NACA 0012 Airfoil at the National Research Council of Canada’s Research Altitude Test Facility

Total Temperature Measurements Using a Rearward Facing Probe in Supercool Liquid Droplet and Ice Crystal Clouds

Kinetic and thermal simulation of water droplets in icing wind tunnels

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