GLTRS--Glenn
TITLE AND SUBTITLE:
Leakage and Power Loss Test Results for Competing Turbine Engine Seals

AUTHOR(S):
Margaret P. Proctor and Irebert R. Delgado

REPORT DATE:
April 2004

FUNDING NUMBERS:
WBS-22-714-09-18

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-14452

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-2004-213049
GT2004-53935

SUPPLEMENTARY NOTES:
Prepared for the Turbo Expo 2004 sponsored by the American Society of Mechanical Engineers, Vienna, Austria, June 14-17, 2004. Margaret P. Proctor, NASA Glenn Research Center; and Irebert R. Delgado, U.S. Army Research Laboratory, NASA Glenn Research Center. Responsible person, Margaret P. Proctor, organization code 5950, 216-977-7526.

ABSTRACT:
Advanced brush and finger seal technologies offer reduced leakage rates over conventional labyrinth seals used in gas turbine engines. To address engine manufacturers' concerns about the heat generation and power loss from these contacting seals, brush, finger, and labyrinth seals were tested in the NASA High Speed, High Temperature Turbine Seal Test Rig. Leakage and power loss test results are compared for these competing seals for operating conditions up to 922 K (1200 °F) inlet air temperature, 517 KPa (75 psid) across the seal, and surface velocities up to 366 m/s (1200 ft/s).

SUBJECT TERMS:
Seals; Brush seal; Finger seal; Labyrinth seal; Leakage; Power loss; Performance

NUMBER OF PAGES:
17

PDF AVAILABLE FROM URL:
2004/TM-2004-213049.pdf ( 1,012 KB )
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