Gas path sealing in turbine enginesSurvey of gas path seals is presented with particular attention given to sealing clearance effects on engine component efficiency. The effects on compressor pressure ratio and stall margin are pointed out. 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 discussed 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
19780049309
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Ludwig, L. P. (NASA Lewis Research Center Cleveland, Ohio, United States)
Date Acquired
August 9, 2013
Publication Date
April 1, 1978
Subject Category
Aircraft Propulsion And Power
Meeting Information
Meeting: Power, Energetics, and Propulsion Panel Meeting on Seal Technology in Gas Turbine Engines, London