1. Propulsion Systems Laboratory
NASA PSL is one of the Nation’s Premier Direct Connect Altitude Simulation Facilities for Full-Scale Gas Turbine Engine and Propulsion System Research
National Research Facility Commercial Development National Defense Initiatives Unique Applications
Capabilities/Applications
Continuous Flow at Full Flight Envelope up to Mach 4, 90,000 ft (-90 F)
Real Time High Speed Data Acquisition and Custom Displays
Six Component Thrust System (50K lbf)
Engine Operability and Stall Resistance
High Altitude Performance
General Aviation and Business Jets
Military Fighter Engine Development
Helicopter Turbo-shaft Engines
UAV/APU/Missile Engines
Engine Icing Research
ice crystal and conventional icing
Williams FJ-33

2. CIP – Cloud Imaging Probe measures particle size
Propulsion Systems Laboratory Jet Engine Icing Enhancement
National Research Facility Commercial Development National Defense Initiatives Unique Applications
Aviation Safety Issue – Studies conclude there are over 140 loss of thrust control incidents thought to be a result of operating in a high altitude ice crystal environment.
NASA Aeronautics Test and Aviation Safety Programs invested in
engine icing research at NASA Glenn’s Propulsion Systems Laboratory
Ice Crystal System
Capabilities
Min
Max
Altitude 4k
40K
Total Temp F
-60 50
Mach #
0.15
0.80
IWC(g/m3)
Ice water content
Cloud Density
0.5
9.0
MWD (µ)
(medium vol. dia) 15 80
Run Time
Continuous
Improve Aviation Safety
Establish the worlds first and only altitude, ice crystal icing engine test facility
Perform fundamental engine icing research to support engine development and help meet newly established engine certification requirements
Develop NPSS engine ice crystal icing risk computer codes
Develop conventional and mixed phase engine icing test capabilities
Collaborate with industry and other government agencies
OBJECTIVES
Williams FJ-33
Spray Nozzles
CIP – Cloud Imaging Probe measures particle size

3. Transition instrumentation & Camera Duct
PSL Engine Icing – Test Cell Hardware Honeywell ALF502-R5 Inaugural Engine Icing Test 2013
Transition instrumentation & Camera Duct
Honeywell ALF 502 installed in PSL3
Flex/Labyrinth Seal
Engine Thrust Stand

4. PSL Engine Icing – Test Cell Hardware Icing Calibration - Instrumentation

5. PSL Engine Icing – Capabilities Four different cloud types to consider in the engine icing arena
Ice Crystals (ICI) new regulation defined in 14 CFR33 Appendix D
Conventional Icing (super-cooled liquid water droplets) (LWC)  defined by 14CFR25 Appendix C
Mixed phased conditions combining both super cooled liquid water droplets and ice crystals
Super cooled large diameter liquid water droplets (SLD) new regulation defined in 14CFR25 Appendix O
The interest from NASA research is the ice accretion, ice shed and ice ingestion into the high pressure compressor of any type of ice building up on the engine induction and compression systems

6. X Altitude 1 Uncommanded Load Reduction Uncommanded N1 Reduction
Cloud on
Cloud off
Uncommanded Load Reduction
Uncommanded N1 Reduction
Static Pressure Reduction
Ice Crystal Icing Engine Testing in the NASA Glenn Research Center’s Propulsion Systems Laboratory (PSL): Altitude Investigation

7. PSL Engine Icing Testing to Date:
Successful inaugural engine icing test (Honeywell ALF502-R5) completed March 2013.
Calibrated and produced known ice crystal conditions in PSL and duplicated a full engine rollback experienced during flight testing on this engine
Generated valuable data used to develop NASA engine icing risk computational tools
Proved out PSL as a viable engine icing R&D test facility
Successful second engine icing test (Proprietary Driven Rig) completed March 2015
Altitude sweeps and various icing cloud conditions
Utilized 20+ internal video camera techniques and specialty non-intrusive instrumentation to document ice accretion and ingestion
Developed ice shedding collection methods
Proved out PSL as a viable large turbofan engine test facility.