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

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

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

PSL Engine Icing – Test Cell Hardware Icing Calibration - Instrumentation

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

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

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.