Actions for Aeropropulsion Technology (APT). Task 23 - Stator Seal Cavity Flow Investigation

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Aeropropulsion Technology (APT). Task 23 - Stator Seal Cavity Flow Investigation

Author
Delaney, R. A.
Published
Dec. 1996.
Physical Description
1 electronic document
Additional Creators
Hall, E. J. and Heidegger, N. J.
Online Version

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Restrictions on Access
Unclassified, Unlimited, Publicly available.
Free-to-read Unrestricted online access
Summary
The focus of NASA Contract NAS3-25950 Task 23 was to numerically investigate the flow through an axial compressor inner-banded stator seal cavity. The Allison/NASA developed ADPAC code was used to obtain all flow predictions. Flow through a labyrinth stator seal cavity of a high-speed compressor was modeled by coupling the cavity flow path and the main flow path of the compressor. A grid resolution study was performed to guarantee adequate grid spacing was used. Both unsteady rotor-stator-rotor interactions and steady-state isolated blade calculations were performed with and without the seal cavity present. A parameterized seal cavity study of the high-speed stator seal cavity collected a series of solutions for geometric variations. The parameter list included seal tooth gap, cavity depth, wheel speed, radial mismatch of hub flowpath, axial trench gap, hub corner treatments, and land edge treatments. Solution data presented includes radial and pitchwise distributions of flow variables and particle traces describing the flow character.
Other Subject(s)
Collection
NASA Technical Reports Server (NTRS) Collection.
Note
Document ID: 19970010484.
Accession ID: 97N15694.
NASA-CR-198504.
NAS 1.26:198504.
E-10340.
Terms of Use and Reproduction
No Copyright.
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