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An analysis of thermal stress and gas bending effects on vibrations of compressor rotor stagesA preliminary study conducted by Kerrebrock et al. (1976) has shown that the torsional rigidity of untwisted thin blades of a transonic compressor can be reduced significantly by transient thermal stresses. The aerodynamic loads have various effects on blade vibration. One effect is that gas bending loads may result in a bending-torsion coupling which may change the characteristics of the torsion and bending vibration of the blade. For a general study of transient-temperature distribution within a rotor stage, a finite-element heat-conduction analysis was developed. The blade and shroud are divided into annular elements. With a temperature distribution obtained from the heat-conduction analysis and a prescribed gas bending load distribution along the blade span, the static deformation and moment distributions of the blade can be solved iteratively using the finite-element method. The reduction of the torsional rigidity of pretwisted blades caused by the thermal stress effect is then computed. The dynamic behavior of the blade is studied by a modified Galerkin's method.
Document ID
19790035485
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Chen, L.-T.
(McDonnell Douglas Research Laboratories St. Louis, Mo., United States)
Dugundji, J.
(MIT Cambridge, Mass., United States)
Date Acquired
August 9, 2013
Publication Date
January 1, 1979
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
AIAA PAPER 79-0045
Meeting Information
Meeting: American Institute of Aeronautics and Astronautics, Aerospace Sciences Meeting
Location: New Orleans, LA
Start Date: January 15, 1979
End Date: January 17, 1979
Sponsors: Astronautics, American Institute of Aeronautics
Accession Number
79A19498
Funding Number(s)
CONTRACT_GRANT: NSG-3079
Distribution Limits
Public
Copyright
Other

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