NDLI: A linear aerodynamic analysis for unsteady transonic cascades

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A linear aerodynamic analysis for unsteady transonic cascades

Content Provider	NASA Technical Reports Server (NTRS)
Author	Caspar, J. R. Verdon, J. M.
Copyright Year	1984
Description	A potential flow analysis to predict unsteady airloads produced by the vibrations of turbomachinery blades operating at transonic Mach numbers is presented. The unsteady aerodynamic model includes the effects of blade geometry, finite mean pressure variation across the blade row, high frequency blade motion, and shock motion within the framework of a linearized, frequency domain formulation. The unsteady equations are solved implicit, least squares, finite difference approximation which is applicable on arbitrary grids. A numerical solution for the entire unsteady field is determined by matching a solution determined on a rectilinear type cascade mesh, which covers an extended blade passage region, to a solution determined on a detailed polar type local mesh, which covers and extends well beyond the supersonic region(s) adjacent to a blade surface. Cascades of double circular arc and flat plate blades demonstrate the unsteady analysis, and partially illustrate the effects of blade geometry, inlet Mach number, blade vibration frequency and shock motion on unsteady response.
File Size	2020675
Page Count	84
File Format	PDF
Alternate Webpage(s)	http://archive.org/details/NASA_NTRS_Archive_19840024285
Archival Resource Key	ark:/13960/t55f3nr1j
Language	English
Publisher Date	1984-09-01
Access Restriction	Open
Subject Keyword	Aerodynamics Turbomachine Blades Cascade Flow Transonic Flow Vibration Deflection Rotor Blades Turbomachinery Least Squares Method Unsteady Aerodynamics Shock Loads Unsteady Flow Two Dimensional Flow Mach Number Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aircraft Aerospace Engineering Aerospace Aeronautic Space Science
Content Type	Text
Resource Type	Technical Report

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