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TITLE AND SUBTITLE:
Further Characterization of an Active Clearance Control Concept
AUTHOR(S):
Taylor, Shawn, C.; Steinetz, Bruce, M.; Oswald, Jay, J.
REPORT DATE:
2007-12-01
FUNDING NUMBERS:
WBS 984754.02.07.03.13.06
PERFORMING ORGANIZATION NAME(S) AND ADDRESS(ES):
National Aeronautics and Space Administration John H. Glenn Research Center at Lewis Field Cleveland, Ohio 44135-3191
PERFORMING ORGANIZATION REPORT NUMBER:
E-16213
SPONSORING/MONITORING AGENCY NAME(S) AND ADDRESS(ES):
National Aeronautics and Space Administration Washington, DC 20546-0001
REPORT TYPE AND DATES COVERED:
Technical Memorandum
SPONSORING/MONITORING AGENCY REPORT NUMBER:
NASA/TM-2007-215039; AIAA-2007-5739
SUPPLEMENTARY NOTES:
ABSTRACT:
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.
SUBJECT TERMS:
Active clearance control; Turbine blades; Gas turbine engines; Temperature
NUMBER OF PAGES:
23
PDF AVAILABLE FROM URL:
2007/TM-2007-215039.pdf ( 1403 KB )
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