Ice Protection of Turbojet Engines by Inertia Separation of Water I : Alternate-duct System

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Summary: Aerodynamic and icing investigations of internal water-inertia separation inlets designed to prevent automatically entrance of large quantities of water into a turbojet engine in icing conditions was conducted on a one-half scale model. A simplified analytical approach to the design of internal water-inertia separation inlets is included. Results show that in order to be effective in preventing screen and guide-vane icing for an inlet of this type, a ram-pressure recovery of 75 percent was attained at design inlet-velocity ratio in an icing condition. For nonicing operation, ram-pressure recovery is comparable to direct-ram inlet.
Collection: NASA Technical Reports Server (NTRS) Collection.
Note: Document ID: 19930085318.
Accession ID: 93R14608.
NACA-RM-E8A27.
Terms of Use and Reproduction: No Copyright.

View MARC record | catkey: 15432575

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