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Gas path sealing in turbine enginesGas path seals are discussed with emphasis on sealing clearance effects on engine component efficiency, compressor pressure ratio, and stall margin. Various case-rotor relative displacements, which affect gas path seal clearances, are identified. Forces produced by nonuniform sealing clearances and their effect on rotor stability are examined qualitatively, and recent work on turbine-blade-tip sealing for high temperatures is described. The need for active clearance control and for engine structural analysis is discussed. The functions of the internal-flow system and its seals are reviewed.
Document ID
19790002886
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Ludwig, L. P.
(NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
August 10, 2013
Publication Date
August 1, 1978
Publication Information
Publication: AGARD Seal Technol. in Gas Turbine Eng.
Subject Category
Aircraft Propulsion And Power
Accession Number
79N11057
Distribution Limits
Public
Copyright
Other
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