NASA LeRC has designed and constructed a new state-of-the-art test facility. This facility, the Transonic Turbine Blade Cascade, is used to evaluate the aerodynamics and heat transfer characteristics of blade geometries for future turbine applications. The facility's capabilities make it unique: no other facility of its kind can combine the high degree of airflow turning, infinitely adjustable incidence angle, and high transonic flow rates. The facility air supply and exhaust pressures are controllable to 16.5 psia and 2 psia, respectively. The inlet air temperatures are at ambient conditions. The facility is equipped with a programmable logic controller with a capacity of 128 input/output channels. The data acquisition system is capable of scanning up to 1750 channels per sec. This paper discusses in detail the capabilities of the facility, overall facility design, instrumentation used in the facility, and the data acquisition system. Actual research data is not discussed.


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    Title :

    Transonic turbine blade cascade testing facility


    Contributors:

    Conference:

    Aerospace Ground Testing Conference ; 1992 ; Nashville, TN, United States


    Publication date :

    1992-01-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English




    Transonic turbine blade cascade testing facility

    VERHOFF, VINCENT / CAMPERCHIOLI, WILLIAM / LOPEZ, ISAAC | AIAA | 1992



    Development of a Large-Scale, Transonic Turbine Blade Cascade Facility for Aerodynamic Studies of Merging Coolant-Mainstream Flows

    Sajben, M. / Al-Sayeh, A. I. / DiMicco, R. G. et al. | British Library Conference Proceedings | 1998