Document
National Aeronautics and Space Administration
NASA Glenn Propulsion Systems Lab
(PSL) Icing Facility Update
Queito P. Thomas
NASA Glenn Research Center SAE 2015 International Conference on Icing of Aircraft, Engines, and Structures, June 22 – 25, 2015 Prague, Czech Republic www.nasa.gov National Aeronautics and Space Administration
Outline
• PSL Background
• PSL Icing Status
• Icing System Design
• Facility Modifications
• Calibration
• Icing Testing Capabilities
www.nasa.gov
PSL Background
NASA PSL is one of the Nation’s Premier Direct Connect Altitude Simulation Facilities for Full - Scale Gas Turbine Engine and Propulsion System Research • Two test sections share common inlet and exhaust • Continuous Operation at high air flow rates Altitude 90,000 ft ( - 90 deg F) PSL - 3 Mach 3.0 (600 deg F) PSL - 4 Mach 4.0 ( 1000 deg F) • PSL3 recently upgraded for icing capability • Multi - axis thrust measurement • Real time, high speed data acquisition and display National Aeronautics and Space Administration 3
NASA PSL Icing Status
• Initial icing calibration completed Nov. 2012
• Inaugural icing test of Honeywell ALF502 -
R5 engine completed April 2013.
• Second icing calibration completed June
2014.
• Second icing test was rig driven and
completed March 2015
• Third icing calibration completed May 2015
National Aeronautics and Space Administration 4
Icing System Design
Specification Min Max Engine / Rig Dia. (in | cm ) 24 | 60 _ 72 | 180 Air Flow Rate ( lbm /s | kg/s ) 10 | 5 _ 330 | 150 Altitude, pressure ( kft | km ) - _ 4 | 1.2 50 | 15 Total Temp ( ° F | ° C ) - 60 | - 50 50 | 10 Mach Number 0.15 0.80 TWC ( g/m ) 0.5 8.0 * # MVD (um) 15 >100 * Evidence that probe under - measured # P articles larger than ≈ 6 0 um are NOT fu l ly glaciated .
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P S L Ici n g Cl o ud H a rdware
S p ray B a rs – C l oud Generation
• T en S p ray B a rs; total of 11 0 Standa r d • n o zzl e s a n d 1 1 2 Mo d 1 n o zzl e s.
• E a ch n ozz l e is i n d i vi d u a lly co n trol l e d .
• N o zzle co n trols: Pai r , atom i zing air pres s ure: 10 – 9 0 psi d, Tair temperature: 45 – 180 F.
P w a t , w ater pres s ure: 10 – 3 00 psid , T w at temperature: 45 – 180 F.
DeltaP = DP = ( P w at – Pa i r) SBCA , Spra y bar cool i ng air .
P : 5 – 40 psid , T : - 40 – 40 F.
(Pa i r, D e lta P ) => (MV D , TW C )
At a given air mass flow rate National Aeronautics and Space Administration 6
Facility Modifications
Steam Injection System is used to provided a constant relative humidity in the inlet plenum to stabilize cloud.
Steam is injected into the inlet airstream as the supply air enters the building.
Relative humidity is measured at the injection point and in the inlet plenum.
National Aeronautics and Space Administration 7
Facility Modifications
Installed Deionized water system for Conventional Icing (CI). Can perform a continuous spray for up to 60 minutes.
• 600 – gallon tank takes 60 – 90 minutes to fill • Monitor resistivity in real - time National Aeronautics and Space Administration 8
Facility Modifications
Tomography laser system installed and used on previous calibrations/tests to measure cloud uniformity.
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Icing Calibration Configurations
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P S L Clouds
• Ice C rys t al s
Cold sp r a y bar air & wa t er te m ps City or De - ionized water Fully glaciated up to MVD 6 0 um Wet Bulb temp < 0 C
• S u percoo l ed Li q uid
Hot s p raybar air & w ater temps
• S u p e rcoo l ed L a rge Dro p s (SLD) , but n ot b i moda l ly
distributed .
National Aeronautics and Space Administration 11
Inaugural Engine Icing Test
Honeywell ALF502R - 5 engine installation in PSL. Validation test was able to replicate both roll back and non - roll back events previously experienced by the engine in flight test.
National Aeronautics and Space Administration 12 Rollback Indicators Chart - roll back test point PSL - 3, FLT850 - 2 Cloud On Initial T/C Decrease 1X TWC Secondary T/C Decrease National Aeronautics and Space Administration 13
Facility Icing Testing Capabilities
• Full sized Engines
Massflows up to 330 pps Exhaust flows up to 500 pps
• Rig Tests
For engines that are too large to fit inside of PSL Successfully completed a booster rig test in 2015 National Aeronautics and Space Administration 14
Summary
• Continuous flow facility • Maintain a constant facility inlet temperature within +/ - 2 deg F • Maintain a constant relative humidity • Vary cloud water content and particle sizes • Run full scale engines • Run LPC Driven Rigs th National Aeronautics and Space Administration 2014 AIAA Aviation - 6 ASE Conf., Jun 2014 15
Questions?/Comments !
Contact Tom Hoffman, PSL Facility Manager 216 - 433 - 5637, thomas.r.hoffman@nasa.gov National Aeronautics and Space Administration 16 National Aeronautics and Space Administration 2014 AIAA Aviation - 6th ASE Conf., Jun 2014 17