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Advanced turbine blade tip seal systemAn advanced blade/shroud system designed to maintain close clearance between blade tips and turbine shrouds and at the same time, be resistant to environmental effects including high temperature oxidation, hot corrosion, and thermal cycling is described. Increased efficiency and increased blade life are attained by using the advanced blade tip seal system. Features of the system include improved clearance control when blade tips preferentially wear the shrouds and a superior single crystal superalloy tip. The tip design, joint location, characterization of the single crystal tip alloy, the abrasive tip treatment, and the component and engine test are among the factors addressed. Results of wear testing, quality control plans, and the total manufacturing cycle required to fully process the blades are also discussed.
Document ID
19810022663
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Zelahy, J. W.
(General Electric Co. Schenectady, NY, United States)
Date Acquired
August 11, 2013
Publication Date
January 1, 1981
Publication Information
Publication: NASA. Lewis Res. Center Aircraft Engine Diagnostics
Subject Category
Aircraft Propulsion And Power
Accession Number
81N31205
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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