NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Collections About News Help Login
Back to Results
Development of an unsteady aerodynamic analysis for finite-deflection subsonic cascadesAn unsteady potential flow analysis, which accounts for the effects of blade geometry and steady turning, was developed to predict aerodynamic forces and moments associated with free vibration or flutter phenomena in the fan, compressor, or turbine stages of modern jet engines. Based on the assumption of small amplitude blade motions, the unsteady flow is governed by linear equations with variable coefficients which depend on the underlying steady low. These equations were approximated using difference expressions determined from an implicit least squares development and applicable on arbitrary grids. The resulting linear system of algebraic equations is block tridiagonal, which permits an efficient, direct (i.e., noniterative) solution. The solution procedure was extended to treat blades with rounded or blunt edges at incidence relative to the inlet flow.
Document ID
19810023577
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Verdon, J. M. (United Technologies Research Center East Hartford, CT, United States)
Caspar, J. R. (United Technologies Research Center East Hartford, CT, United States)
Date Acquired
September 4, 2013
Publication Date
September 1, 1981
Subject Category
Aerodynamics
Report/Patent Number
R81-914777-7
NASA-CR-3455
Accession Number
81N32120
Funding Number(s)
PROJECT: RTOP 510-55-12
CONTRACT_GRANT: NAS3-21981
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

Related Records

There are no records associated with this record.
No Preview Available