The concept of blunt trailing edge blading for use in supersonic axial compressors is described, and its expected advantages and disadvantages are discussed. Its basic features - the possibility of decelerating a supersonic flow to subsonic velocities by means of a multiple shock system - are shown to be valid, as well as the possibility of having efficient deceleration by a sudden increase in flow passage area, if this change of area is kept within certain limits. Use of a constantly diverging section proves beneficial for operation in subsonic, transonic and supersonic flows. The advantage of using a twisted blading for the rotor is shown by the experimental results. Satisfactory cascade, rotor and stage performances were obtained with a wide range of bladings using the concept, from subsonic to supersonic speeds. Its potential could be used in both low and high hub to tip ratio supersonic compressor stages. (Author)


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    Title :

    Note on the Concept of Blunt Trailing Edge Blades


    Contributors:
    J. Chauvin (author) / F. Breugelmans (author)

    Publication date :

    1967


    Size :

    37 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English




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