Engine Inlet Icing

"The desirability for all-weather operation of turbojet aircraft has necessitated extensive research on methods of icing protection for the various engine components"

Figure 3b. Ice formation on axial-flow turbojet engine. Side view of ice formation on engine inlet.
From NACA-RM-E8C18.

Discussion

Publications taken largely from The Historical Selected Bibliography of NACA-NASA Icing Publications, "Turbine-Type Engine and Inlet Icing Studies" section are reviewed here.

Reviews

NACA-TN-1246 "Wind-Tunnel Investigation of Icing of an Engine Cooling-Fan Installation"

  • "The icing of the unprotected installation presents a serious operational problem"

NACA-RM-E8C18 "Preliminary Results of Natural Icing of an Axial-Flow Turbojet Engine"

  • "Ice formations penetrated to the second-stage rotor blades"

NACA-RM-E8FO1a "Natural Icing of an Axial-Flow Turbojet Engine in Flight for a Single Icing Condition"

  • "The engine was satisfactorily accelerated to take-off power after approximately 45 minutes in the icing condition"

NACA-TN-2126 "Improvements in Heat Transfer for Anti-Icing of Gas-Heated Airfoils with Internal Fins and Partitions"

  • "Use of the hot-gas method of anti-icing has been restricted ... because of difficulty in controlling the rate of heat dissipation"

NACA-RM-E50I08 "Icing Characteristics and Anti-Icing Heat Requirements for Hollow and Internally Modified Gas-Heated Inlet Guide Vanes"

  • "Ice formations ... may have the following effects, which when combined may become serious enough to necessitate a shutdown of the engine: reduced engine thrust, increased,fuel consumption, and increased tail-pipe temperature"

NACA-RM-E50E03 "Investigation of Aerodynamic and Icing Characteristics of Water-Inertia-Separation inlets for Turbojet Engines"

  • "Complete icing protection for inlet guide vanes of a turbojet engine could not be achieved"

NACA-RM-E50H29 "Investigation of Power Requirements for Ice Prevention and Cyclical De-Icing of Inlet Guide Vanes with Internal Electric Heaters"

  • "Experience has shown that ... the inlet guide vanes of an axial-flow turbojet engine constitute the most critical component to be protected from icing"

NACA-RM-E51B12 "NACA Investigations of Icing-Protection Systems for Turbojet-Engine Installations"

  • "Serious icing of a turbojet-engine installation may render the engine inoperative in a matter of minutes."

NACA-TN-3837 "Investigation of Heat Transfer from a Stationary and Rotating Ellipsoidal Forebody of Fineness Ratio 3"

  • "Many aircraft components are essentially simple bodies of revolution; examples of these are radomes, body noses, engine accessory housings, and the large spinners of turboprop engines"

NACA-TN-4093 "Investigation of Heat Transfer from a Stationary and Rotating Conical Forebody"

  • "Rotational speeds up to 1200 rpm had no apparent effect on the heat-transfer characteristics of the spinner"

NACA-RM-E57G09 "Total Pressure Distortion and Recovery of Supersonic Nose Inlet with Conical Centerbody in Subsonic Icing Conditions"

  • "the contour plots indicate that cowl-lip disturbances are the more controlling factor"

Related

There is also

  • von Glahn, Uwe H.: Preliminary Results of Heat Transfer from a Stationary and Rotating Ellipsoidal Spinner. NACA-EM-E53F02, 1953.

However, this was largely a preliminary version of NACA-TN-3837 "Investigation of Heat Transfer from a Stationary and Rotating Ellipsoidal Forebody of Fineness Ratio 3", and so it will not be separately reviewed.

See also:

Ice Protection Thread
Impingement in Ducts
Impingement in Engine Inlets

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