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energy efficient engine high pressure turbine test hardware detailed design reportThe high pressure turbine configuration for the Energy Efficient Engine is built around a two-stage design system. Moderate aerodynamic loading for both stages is used to achieve the high level of turbine efficiency. Flowpath components are designed for 18,000 hours of life, while the static and rotating structures are designed for 36,000 hours of engine operation. Both stages of turbine blades and vanes are air-cooled incorporating advanced state of the art in cooling technology. Direct solidification (DS) alloys are used for blades and one stage of vanes, and an oxide dispersion system (ODS) alloy is used for the Stage 1 nozzle airfoils. Ceramic shrouds are used as the material composition for the Stage 1 shroud. An active clearance control (ACC) system is used to control the blade tip to shroud clearances for both stages. Fan air is used to impinge on the shroud casing support rings, thereby controlling the growth rate of the shroud. This procedure allows close clearance control while minimizing blade tip to shroud rubs.
Document ID
19850002687
Document Type
Contractor Report (CR)
Authors
Halila, E. E.
(General Electric Co. Cincinnati, OH, United States)
Lenahan, D. T.
(General Electric Co. Cincinnati, OH, United States)
Thomas, T. T.
(General Electric Co. Cincinnati, OH, United States)
Date Acquired
September 5, 2013
Publication Date
June 1, 1982
Subject Category
AIRCRAFT PROPULSION AND POWER
Report/Patent Number
NASA-CR-167955
NAS 1.26:167955
R81AEG284
Funding Number(s)
CONTRACT_GRANT: NAS3-20643
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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