Document
National Aeronautics and Space Administration
NASA Icing Update
Presentation (virtual) to the:
Ice Crystal Consortium (ICC)
November 9, 2022
Contributors:
Judy Van Zante, Mike Oliver, Rick Bozak
Emily Timko (Jacobs), Ru - Ching Chen,
Tadas Bartkus (OAI), Christopher Porter
NASA Glenn Research Center
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Agenda
• Introduction / Background
• Facility Update
– Propulsion Systems Lab
– Icing Research Tunnel
– Adaptive Icing Tunnel
• Experiment Update:
– Simulated Inter - compressor Duct Research Model (SIDRM)
• Simulation & Experimental Tools
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Icing Work across NASA Aero Projects
Aerosciences Evaluation and Test Advanced Air Vehicles Transformative Aeronautics Capabilities Portfolio Program Concepts Program AAVP Projects TACP Projects AETC Portfolio Office * Advance Air Transport Tech (AATT) Convergent Aeronautics Solutions (CAS) Portfolio Facilities with Icing * * Vehicle System Integration (VSI) Transformational Tools and Tech (TTT) Icing Research Tunnel (IRT) * Power & Propulsion (P&P) Reduced Life Cycle Cost (RLCC)* Propulsion Systems Lab (PSL) Commercial Supersonic Tech (CST) University Innovation (UI) Operations Hi - Rate Composite Aircraft Mfg. ( HiCAM ) Maintenance Hybrid Thermally Efficient Core ( HyTEC ) * Capabilities Improvement Hypersonic Tech (HT) Data Systems and Security * Icing work currently in these * Revolutionary Vertical Lift Tech (RVLT) Computational Fluid Dynamics and Test projects / subprojects Integration www.nasa.gov National Aeronautics and Space Administration
PSL Update
POC: Judy Van Zante
Mike Oliver, Rick Bozak
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PSL: Propulsion Systems Lab
Engine Test Stand with Altitude and Ice Crystal Capability
Bulkhead w/ NASA - owned Engine Plenum with Spray Bars,
contraction duct (to F = 3 - ft) F = 18 - ft
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PSL Ranges for Engine or Driven Rig
Conditions: User supplies:
Duct Geometry Dia : 24 to 84 in Static Pres, static Temp, Mach No. &
Mass Flow Rate at plane of interest.
Pressure Altitude: 4 to 40 kft
TWC, MVD ranges
Mach: 0.15 to 0.8
Air Mass Flow Rate: 50 to 330 lbm /s
Temperature: - 50 to +50 F
Relative Humidity: 3 to 50%
36 - in duct calibration configuration
Bulkhead www.nasa.gov National Aeronautics and Space Administration
Ice Crystal & Icing Cloud
NASA will calibrate TWC and MVD for test -
App D Cal Regimes to date
specific ranges in App D, App C & App O.
Most calibrations to date have been in the
36 - in duct.
Two atmospheric conditions have been
simulated : Flight and Core Flow Path.
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Cloud Calibration Plan
• Investigate ability to produce IC with DI water.
• Investigate new IC characterization instrumentation.
• Calibrate IC cloud in "flight" environment (higher altitude,
tropical day)
• Calibrate cloud in "core" flow path conditions (lower
altitude, Twb near 0C)
• Calibrate SCL cloud for fan testing
Nomenclature DI De - ionized IC Ice Crystal SCL Supercooled Liquid Twb Wet Bulb Temp.
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PSL Plans – Icing
• Proposed Icing Plans
• Re - install icing spray bars
• C onduct a cloud calibration
• Collaborate with an engine manufacturer to expand and validate capabilities
• Proposed Future Goals: Expand Icing Test Capabilities
• Free Jet Icing Capability
• Impact of alternative ducting (e.g. turboshaft)
• Transient testing, including snap accels
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IRT Update
POC: Emily Timko
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IRT: Icing Research Tunnel
• Test section size: 6 ft. x 9 ft. (1.8 m x 2.7 m) • Calibrated MVD range: 14 – 270 μm • LWC & MVD calibration measurements are • Calibrated LWC range: 0.17 – 4.0 g/m (function of airspeed) • Two types of spray nozzles: made in the center of the test section • LWC uniformity: ± 10% for central 4 ft x 6 ft • Standards = higher water flow rate • Mod1 = lower water flow rate • Calibrated test section airspeed: 50 – 300 kts • Air temperature: - 35ºC static to +15ºC total www.nasa.gov National Aeronautics and Space Administration
IRT Calibration
• SAE's ARP5905 "Calibration and Acceptance of
Icing Wind Tunnels"
• 5 - year calibration interval
• Check calibrations every 6 months
• Interim calibration 1 year after full calibration
• Full calibration performed in 2019
Calibration report available upon request
• Calibration done for Appendix C and Appendix O
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Potential Ice Crystal Capabilities
• Increasing demand • Researchers, outside customers, facility engineers • Efforts have begun • Phase repeatability analysis • Characterization focused on specific research tests • Test entries on schedule to evaluate uniformity, ice water content, and particle sizes • Ice Crystal Cloud Challenges • How to develop uniformity • Particle size instrumentation for smaller, frozen particles • Recirculation of accumulated ice particles • Facility Challenges • Spraybar air and water supply can only be "not heated" • Technology and development to be able to cool the supply • Unheated supplies also result in frozen nozzles • Ice crystals left in tunnel loop • Quantifying recirculation effects www.nasa.gov National Aeronautics and Space Administration
Adaptive Icing Tunnel (AIT)
POC: Ru - Ching Chen
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What is the Adaptive Icing Tunnel (AIT)
• Closed loop, vertical refrigerated
Lower - cost capability for instrument
icing wind tunnel
evaluation and proof - of - concept testing.
• Test section:
– 1’ x 1’ cross section
– 2’ long
– Flow speeds of ~210 knots (~110 m/s)
– Temperatures as cold as - 20 ° C
• Walk - in freezer surrounding test
section
• Planning for supercooled water and
ice crystal capability
• Scheduled for installation in FY23
followed by tunnel characterization
www.nasa.gov National Aeronautics and Space Administration Removable Heat Exchanger Turning vanes
Adaptive Icing Tunnel
Cross Section
Removable spray bar 1’ x 1’ x 2’ Test Section Fan blades accessible via Panel Removable corners and diffuser www.nasa.gov National Aeronautics and Space Administration
Simulated Inter - compressor Duct
Research Model (SIDRM)
Project Sponsor: AATT P&P
POC: Tadas Bartkus
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IRT Ice Crystal Cloud Characterization and SIDRM Icing Tests
Problem Turbofan power - loss or damage events attributed to ice crystals . 3 D computational engine icing tools, such as GlennICE, require validation data .
Objective Develop a test article - the Simulated Inter - compressor Duct Research Model (SIDRM) – representative of a compressor strut - duct interface . Generate and measure supercooled liquid and ice crystal icing accretions under well characterized conditions to develop and validate 3 D icing tools .
Approach 1. Identify and characterize ice crystal clouds in Icing Research Tunnel (IRT) .
Flow 2. Supercooled liquid water testing 3. Ice crystal test testing using a heated surface .
SIDRM vertical orientation in IRT tunnel with multiple viewing windows Significance These tests represent the first time that ice accretions were measured on a 3 D test article at IRT . Using an open geometry configuration, these tests recreated ice crystal icing features characteristic of those seen in previous engine icing tests .
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SIDRM Test Article
1.59 m SIDRM profile view 0.55 m Flow Flow Generic engine schematic https://arc.aiaa.org/doi/abs/10.2514/6.2022 - 3700 https://ntrs.nasa.gov/citations/20220006460 www.nasa.gov National Aeronautics and Space Administration
Primary Instruments and Measurements
SIDRM Built - In Instruments • 64 Pressure taps • 43 Thermocouples • 11 Heat flux gauges • 6 Independently controlled heater zones (main body) External Instruments • 3D laser scanner • Scale to weigh accreted ice mass • Video and digital cameras View of TCs and pressure taps Heated zones of main body www.nasa.gov National Aeronautics and Space Administration
SIDRM Supercooled Liquid Icing and Ice Crystal Icing Tests
Results In 2022 , characterized numerous ice crystal cloud conditions at IRT and conducted 61 icing tests, providing validation data for 3 D computational icing tools .
Significance These tests represent the first time that ice accretions were measured on a 3 D test article at IRT . Using an open geometry configuration, these tests recreated ice crystal icing features characteristic of those seen in previous engine icing tests .
Ice crystal icing utilizing SIDRM’s Supercooled liquid ice heated panels with zoomed in view of accretion on SIDRM “sharkteeth” https://arc.aiaa.org/doi/abs/10.2514/6.2022 - 3700 https://ntrs.nasa.gov/citations/20220006460 www.nasa.gov National Aeronautics and Space Administration
Supercooled Liquid Icing Analysis
• Ice mass weighed – center 8” span • 3D laser scan – center 10” span • Identify parameters and interpret the physics that influence accretion size, location, and quality.
Centerline cross sections at the SIDRM leading edge www.nasa.gov National Aeronautics and Space Administration
Ice Crystal Cloud Characterization at IRT
• Ice crystal generation is not well characterized at IRT • Well characterized cloud needed to properly model resulting icing data • Objective : Identify glaciated conditions and characterize IC cloud using following instrument suite • 13 days of testing identified and characterized 12 conditions O • Ice crystal cloud envelope limited to colder (T0 < - 15 C), and smaller diameter (MVD < 43 μm).
• Repeated tests and recirculation important Test Section Instrument Measurement Multiwire (SEA) Melt ratio & recirculation Isokinetic Probe (SEA) Total water content & recirculation Rearward Facing Probe Air temperature and humidity Particle Imaging – Ice Crystal probe (Artium) Particle size distribution Particle Tracking Velocimetry probe (Artium) Particle velocity TAT probe (Rosemount) Air temperature Ice Detector probe (UTC Aerospace) Glaciation (liquid presence) Flow Background Humidity Bent Tube probe Humidity Light Extinction Probe Recirculation Various probes installed in the NASA IRT test section https://arc.aiaa.org/doi/abs/10.2514/6.2022 - 3700 during IC cloud characterization tests in Feb 2022 https://ntrs.nasa.gov/citations/20220006460 www.nasa.gov National Aeronautics and Space Administration
NASA Computational Tools
Project Sponsors: AATT/P&P & VSI, TTT/RLCC
POC: Christopher Porter
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NASA Icing Tools
LEWICE • 2D tool that evaluates the freezing process thermodynamics that occur when super - cooled droplets impinge on a body and generate a 2D ice shape.
• https://software.nasa.gov/software/LEW - 18573 - 1 LEWICE3D • Quasi - 3D tool that computes the trajectories and impingement in 3D, but uses a strip - theory assumption to compute the mass/energy balance and ice growth on user specified cut planes.
• https://software.nasa.gov/software/LEW - 19433 - 1 COMDES - MELT: A Turbofan Engine Icing Risk Analysis Tool • Mean - line compressor analysis code coupled with an ice crystal thermodynamic state code.
• https://software.nasa.gov/software/LEW - 20027 - 1 TADICE • One dimensional (1D) numerical model simulates icing wind tunnels by modeling the thermodynamic interactions between the water/ice particles of an icing cloud and the flowing air.
• https://software.nasa.gov/software/LEW - 19874 - 1 Multiscale Modeling • A seedling effort investigating multiscale modeling for icephobic research.
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GlennICE
Non - Rotating Reference Frame AAM test stand Rotating Reference Frame GlennICE simulation of the AAM test stand .
A full 3D GlennICE simulation of an ice accretion due to a 15 μm cloud on the Depiction of the differences in trajectory representation in a rotating and non - rotating TTBW. Insets depict the accretion on the engine inlet, with the line plot reference frame (left). Demonstration of the rotating reference frame additions on the including a comparison to the legacy quasi - 3D icing software, LEWICE3D.
Advance Air Mobility (AAM) test stand geometry (right).
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