Techniques have been developed at the Engine Test Facility (ETF) of the Arnold Engineering Development Center (AEDC) to simulate flight through atmospheric icing conditions of supercooled liquid water droplets. Ice formed on aircraft and propulsion system surfaces during flight through icing conditions can, even in small amounts, be extremely hazardous. The effects of ice are dependent on many variables and are still unpredictable. Often, experiments are conducted to determine the characteristics of the aircraft and its propulsion system in an icing environment. Facilities at the ETF provide the capability to conduct icing testing in either the direct-connect (connected pipe) or the free-jet mode. The requirements of a spray system for turbine engine icing testing are described, as are the techniques used at the AEDC ETF to simulate flight in icing conditions. Some of the key issues facing the designer of a spray system for use in an altitude facility are identified and discussed, and validation testing of the design of a new spray system for the AEDC ETF is detailed. This spray system enables testing of the newest generation of high-thrust turbofan engines in simulated icing conditions.

Issue Section:
Gas Turbines: Aircraft
Topics:
Design, Gas turbines, Sprays, Testing, Flight, Aircraft, Engines, Ice, Propulsion systems, Drops, Pipes, Test facilities, Thrust, Turbofans, Water
1.
Ashendon, R. A., 1993, “The Air Force Flight Test Center Artificial Icing and Rain Testing Capability Upgrade Program,” AIAA Paper No. 93-0295.
2.
Bartlett, C. S., 1988, “Icing Scaling Considerations for Aircraft Engine Testing,” AIAA Paper No. 88-0202.
3.
Bartlett, C. S., et al., 1990, “Icing Test Capabilities for Propulsion Systems at the Arnold Engineering Development Center,” AGARD-CP-480.
4.
Bartlett, C. S., and Phares, W. J., 1993, “Icing Testing of a Large Full Scale Inlet at the Arnold Engineering Development Center,” AIAA Paper No. 93-0299.
5.
Belte, D., and Woratschek, R., 1986, “Helicopter Icing Spray System Evaluation and Improvements,” USAAEFA 82-05-3.
6.
Federal Aviation Administration, Federal Aviation Regulation, Part 25, 1984, “Airworthiness Standards: Transport Category Airplanes: Appendix C.”
7.
Gall, E. S., and Floyd, F. X., 1971, “Icing Test Capability of the Engine Test Facility Propulsion Development Test Cell (J-1),” AEDC-TR-71-94 (AD-729205).
8.
Gelder, T. F., 1958, “Droplet Impingement and Ingestion by Supersonic Nose Inlet in Subsonic Tunnel Conditions,” NACA TN 4268.
9.
Hunt, J. D., 1978, “Engine Icing Measurement Capabilities at the AEDC,” AGARD-CP-236.
10.
Pheifer, G. D., and Maier, G. P., 1977, “Engineering Summary of Powerplant Icing Technical Data,” FAA-RD-77-76.
11.
Willbanks, C. E., and Schulz, R. J., 1973, “Analytical Study of Icing Simulation for Turbine Engines in Altitude Test Cells,” AEDC-TR-73-144 (AD-770069).
This content is only available via PDF.
Copyright © 1995
 by The American Society of Mechanical Engineers
You do not currently have access to this content.