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TITLE AND SUBTITLE:
High Temperature Evaluation of an Active Clearance Control System Concept
AUTHOR(S):
Taylor, Shawn, C.; Steinetz, Bruce, M.; Oswald, Jay, J.
REPORT DATE:
2006-11-XX
FUNDING NUMBERS:
WBS 984754.02.07.03.07.02
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-15727
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-2006-214464
SUPPLEMENTARY NOTES:
Prepared for the 42nd Joint Propulsion Conference and Exhibit cosponsored by AIAA, ASME, SAE, and ASEE, Sacramento, California, July 9-12, 2006. Shawn C. Taylor, 2801 W. Bancroft St., Toledo, Ohio 43606; Bruce M. Steinetz, Glenn Research Center; and Jay J. Oswald, J&J Technical Solutions, 14880 Timber Lane, Cleveland, Ohio 44130. Responsible person, Shawn C. Taylor, organization code RXM, 216-433-3166.
ABSTRACT:
A mechanically actuated blade tip clearance control concept was evaluated in a nonrotating test rig to quantify secondary seal leakage at elevated temperatures. These tests were conducted to further investigate the feasibility of actively controlling the clearance between the rotor blade tips and the surrounding shroud seal in the high pressure turbine (HPT) section of a turbine engine. The test environment simulates the state of the back side of the HPT shroud seal with pressure differentials as high as 120 psig and temperatures up to 1000 ºF. As expected, static secondary seal leakage decreased with increasing temperature. At 1000 ºF, the test rig's calculated effective clearance (at 120 psig test pressure) was 0.0003 in., well within the industry specified effective clearance goal.
SUBJECT TERMS:
Seals; Flow; Design; Test; High temperature; Clearance control; Turbine; Actuators
NUMBER OF PAGES:
20
PDF AVAILABLE FROM URL:
2006/TM-2006-214464.pdf ( 1386 KB )
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