Pertinent items relating to the design of internal-flow systems for reciprocating engine, turbine engine, and pressure-jet installations in helicopters are discussed. The importance of the following items is emphasized: controllable exit and ram recovery for reciprocating-engine cooling; performance penalties possible in turbine-engine installations attributed to distortions in the flow distribution at the face of the axial compressor; the effects of high subsonic flow velocities on the performance of duct elements; and the effects of centrifugal forces on the flow in a ducted helicopter rotor. Data on the maximum flow capacities of bends are included.


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    Title :

    Aspects of Internal-Flow-System Design for Helicopter Propulsive Units


    Contributors:

    Publication date :

    1954-09-14


    Type of media :

    Miscellaneous


    Type of material :

    No indication


    Language :

    English




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