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Thermal stress analysis of a new turbine shroud seal concept

Author
Handschuh, R. F.
Published
Aug 1, 1985.
Physical Description
1 electronic document
Online Version

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Unclassified, Unlimited, Publicly available.
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Summary
The thermal stress field of a two piece turbine shroud seal concept was analyzed and results compared to one piece designs by finite element analysis. The two piece seal has independently formed structure (substrate) and ceramic components that are assembled at ambient conditions. The boundary conditions used for analysis were hot gas surface temperatures of 1370 and 1650 C (2500 and 3000 F) and cooled surface temperature of 700 C (1285 F). The resulting thermal stress field, of the two piece seal when compared to the one piece seals in the region of all ceramic material, was reduced substantially.
Other Subject(s)
Collection
NASA Technical Reports Server (NTRS) Collection.
Note
Document ID: 19850026093.
Accession ID: 85N34406.
NAS 1.15:87082.
E-2666.
USAAVSCOM-TR-85-C-16.
NASA-TM-87082.
Terms of Use and Reproduction
No Copyright.
View MARC record | catkey: 15704140