GLTRS--Glenn
TITLE AND SUBTITLE:
Advanced Seal Technology Role in Meeting Next Generation Turbine Engine Goals

AUTHOR(S):
Bruce M. Steinetz, Robert C. Hendricks, and John Munson

REPORT DATE:
April 1998

FUNDING NUMBERS:
WU-538-12-20-00

PERFORMING ORGANIZATION NAME(S) AND ADDRESS(ES):
National Aeronautics and Space Administration
Lewis Research Center
Cleveland, Ohio 44135-3191

PERFORMING ORGANIZATION REPORT NUMBER:
E-11109

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-1998-206961
AVT-PPS Paper No. 11

SUPPLEMENTARY NOTES:
Prepared for the Propulsion and Power Systems First Meeting on Design Principles and Methods for Aircraft Gas Turbine Engines sponsored by the NATO Research and Technology Agency, Toulouse, France, May 11-15, 1998. Bruce M. Steinetz and Robert C. Hendricks, NASA Lewis Research Center; John Munson, Allison Engine Company, Indianapolis, Indiana. Responsible person, Bruce M. Steinetz, organization code 5950, (216) 433-3302.

ABSTRACT:
Cycle studies have shown the benefits of increasing engine pressure ratios and cycle temperatures to decrease engine weight and improve performance in next generation turbine engines. Advanced seals have been identified as critical in meeting engine goals for specific fuel consumption, thrust-to-weight, emissions, durability and operating costs. NASA and the industry are identifying and developing engine and sealing technologies that will result in dramatic improvements and address the goals for engines entering service in the 2005-2007 time frame. This paper provides an overview of advanced seal technology requirements and highlights the resultsof a preliminary design effort to implement advanced seals into a regional aircraft turbine engine. This study examines in great detail the benefits of applying advanced seals in the high pressure turbine region of the engine. Low leakage film-riding seals can cut in half the estimated 4% cycle air currently used to purgethe high pressure turbine cavities. These savings can be applied in one of several ways. Holding rotor inlet temperature (RIT) constant the engine specific fuel consumption can be reduced 0.9%, or thrust couldbe increased 2.5%, or mission fuel burn could be reduced 1.3%. Alternatively, RIT could be lowered 20 °F resulting in a 50% increase in turbine bladelife reducing overall regional aircraft maintenance and fuel burn direct operating costs by nearly 1%. Thermal, structural, secondary-air systems, safety (seal failure and effect), and emissions analyses have shown the proposed design is feasible.

SUBJECT TERMS:
Seals; Design; Turbine engine

NUMBER OF PAGES:
17

PDF AVAILABLE FROM URL:
1998/TM-1998-206961.pdf
( 429 KB )

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