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Energy efficient engine. Low pressure turbine test hardware detailed design reportThe low pressure turbine for the energy efficient engine is a five-stage configuration with moderate aerodynamic loading incorporating advanced features of decambered airfoils and extended blade overlaps at platforms and shrouds. Mechanical integrity of 18,000 hours on flowpath components and 36,000 hours on all other components is achieved along with no aeromechanical instabilities within the steady-state operating range. Selection of a large number (156) of stage 4 blades, together with an increased stage 4 vane-to-blade gap, assists in achieving FAR 36 acoustic goals. Active clearance control (ACC) of gaps at blade tips and interstage seals is achieved by fan air cooling judiciously applied at responsive locations on the casing. This ACC system is a major improvement in preventing deterioration of the 0.0381 cm (0.015 in.) clearances required to meet the integrated-core/low-spool turbine efficiency goal of 91.1% and the light propulsion system efficiency goal of 91.7%.
Document ID
19850002686
Document Type
Contractor Report (CR)
Authors
Cherry, D. G. (General Electric Co. Cincinnati, OH, United States)
Gay, C. H. (General Electric Co. Cincinnati, OH, United States)
Lenahan, D. T. (General Electric Co. Cincinnati, OH, United States)
Date Acquired
September 5, 2013
Publication Date
August 1, 1982
Subject Category
AIRCRAFT PROPULSION AND POWER
Report/Patent Number
NAS 1.26:167956
NASA-CR-167956
R81AEG597
Funding Number(s)
CONTRACT_GRANT: NAS3-20643
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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