A new test chamber and precision hydraulic actuation system were incorporated into an active clearance control (ACC) test rig at NASA Glenn Research Center. Using the improved system, a fast-acting, mechanically-actuated, ACC concept was evaluated at engine simulated temperatures and pressure differentials up to 1140 F and 120 psig, on the basis of secondary seal leakage and kinematic controllability. During testing, the ACC concept tracked a simulated flight clearance transient profile at 1140 F, 120 psig, with a maximum error of only 0.0012 in. Comparison of average dynamic leakage of the system with average static leakage did not show significant differences between the two operating conditions. Calculated effective clearance values for the rig were approximately 0.0002 in. at 120 psig, well below the industry specified effective clearance threshold of 0.001 in.


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    Title :

    Further Characterization of an Active Clearance Control Concept


    Contributors:

    Conference:

    43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit ; 2007 ; Cincinnati, OH, United States


    Publication date :

    2007-12-01


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English




    Further Characterization of an Active Clearance Control System Concept

    Taylor, Shawn / Steinetz, Bruce / Oswald, Jay | AIAA | 2007


    Further Characterization of an Active Clearance Control System Concept AIAA Paper

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    High Temperature Evaluation of an Active Clearance Control System Concept

    Taylor, Shawn / Steinetz, Bruce / Oswald, Jay | AIAA | 2006