Icing test capabilities for full-scale turbine engine propulsion systems have been developed in the Engine Tst Facility (ETF) at the Arnold Engienering Development Center (AEDC). The current capability to simulate natural in-flight icing environments includes knowledge and control of the principal factors that govern the mechanics and thermodynamics of icing, namely, water droplet size distribution, liquid water content, cloud temperature, pressure, and propulsion system airflow rates. The AEDC facilities provide the capability to conduct evaluation tests in either the direct-connect or free-jet mode. The methods and hardware used to inject liquid spray into a cold airstream to simulate inflight icing conditions are discussed. The spray manifold systems and spray injection nozzles currently in use at AEDC are described. The methods used to operate and control the cloud generation systems are given. Pulsed-laser and pinhole viewing techniques used to view rotating engine hardware in freeze-frame, and low-light cameras could with fiber-optics used to penetrate to the inner recess of inlet system to observe real-time transient icing processes on surfaces susceptible to icing are described. Test experiences in both direct and free-jet connect icing testing are addressed.
Icing test capabilities for aircraft propulsion systems at the Arnold engineering development center
Prüfung der Vereisungsleistung bei Flugzeugturbinen im Arnolds-Entwicklungszentrum für Technik
1990
9 Seiten, 11 Bilder, 1 Tabelle, 10 Quellen
Conference paper
English
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