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A Three-Dimensional Linearized Unsteady Euler Analysis for Turbomachinery Blade RowsA three-dimensional, linearized, Euler analysis is being developed to provide an efficient unsteady aerodynamic analysis that can be used to predict the aeroelastic and aeroacoustic responses of axial-flow turbo-machinery blading.The field equations and boundary conditions needed to describe nonlinear and linearized inviscid unsteady flows through a blade row operating within a cylindrical annular duct are presented. A numerical model for linearized inviscid unsteady flows, which couples a near-field, implicit, wave-split, finite volume analysis to a far-field eigenanalysis, is also described. The linearized aerodynamic and numerical models have been implemented into a three-dimensional linearized unsteady flow code, called LINFLUX. This code has been applied to selected, benchmark, unsteady, subsonic flows to establish its accuracy and to demonstrate its current capabilities. The unsteady flows considered, have been chosen to allow convenient comparisons between the LINFLUX results and those of well-known, two-dimensional, unsteady flow codes. Detailed numerical results for a helical fan and a three-dimensional version of the 10th Standard Cascade indicate that important progress has been made towards the development of a reliable and useful, three-dimensional, prediction capability that can be used in aeroelastic and aeroacoustic design studies.
Document ID
19970014823
Document Type
Contractor Report (CR)
Authors
Montgomery, Matthew D. (United Technologies Corp. East Hartford, CT United States)
Verdon, Joseph M. (United Technologies Corp. East Hartford, CT United States)
Date Acquired
September 6, 2013
Publication Date
March 1, 1997
Subject Category
Aircraft Propulsion and Power
Report/Patent Number
E-10670
NAS 1.26:4770
NASA-CR-4770
Funding Number(s)
CONTRACT_GRANT: NAS3-26618
PROJECT: RTOP 538-03-11
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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