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    Two-Stage Axial Compressor Rig Designed To Develop and Validate Advanced Aerodynamic Technologies (2003)
    In:  CASI
    Details
    Publication Date: 2018-06-02
    Description: Future aeropropulsion gas turbine engines must be affordable in addition to being energy efficient and environmentally benign. Progress in aerodynamic design capability is required not only to maximize the specific thrust of next-generation engines without sacrificing fuel consumption, but also to reduce parts count by increasing the aerodynamic loading of the compression system. To meet future compressor requirements, the NASA Glenn Research Center is investigating advanced aerodynamic design concepts that will lead to more compact, higher efficiency, and wider operability configurations than are currently in operation.
    Keywords: Aircraft Propulsion and Power
    Type: Research and Technology 2002; NASA/TM-2003-211990
    Format: application/pdf
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