An Analytical Approach To Designing Friction Dampers In Turbomachinery Blading
Report Number: WL-TR-91-3078 Volume III, p. JBA-1 thru JBA-14
Author(s): Panovsky, Josef, Hendley, David O., MacKay, Raymond A.
Corporate Author(s): GE Aircraft Engines, Cincinnati, Ohio and Lynn, Massachusetts
Date of Publication: 1991-08
Pages: 14
DoD Task:
Identifier: This paper is part of a conference proceedings. See ADA241313
Abstract:
Aircraft engine turbomachinery blading operates in an environment that induces vibration which can lead to failure through high-cycle fatigue. This vibration can often be reduced to acceptable levels by friction dampers, which dissipate energy by capitalizing on the resulting relative motion between the blade and a motionless structure or adjacent vibrating blades. The key to optimizing a given damper design is to determine the dynamic weight at which the maximum energy is dissipated without locking the blade at the damper contact point. As the design of turbomachinery blading progresses towards higher-loaded stages with more complex geometry, vibratory modes beyond the primary beam bending become more prominent. This pape will discuss the development of an analytical method to predict damper effectlveness for any blade mode. The analysis is based on a component mode method, and includes provisions for modeling stick-slip at the friction contact. Multiple damper contact points can be evaluated, and the damper design can be blade-to-ground or blade-to-blade with arbitrary phase angle. The results of a series of lab tests with simple beam specimens to evaluate the principal damper design variables will be presented along with the corresponding analytical predictions.
Author(s): Panovsky, Josef, Hendley, David O., MacKay, Raymond A.
Corporate Author(s): GE Aircraft Engines, Cincinnati, Ohio and Lynn, Massachusetts
Date of Publication: 1991-08
Pages: 14
DoD Task:
Identifier: This paper is part of a conference proceedings. See ADA241313
Abstract:
Aircraft engine turbomachinery blading operates in an environment that induces vibration which can lead to failure through high-cycle fatigue. This vibration can often be reduced to acceptable levels by friction dampers, which dissipate energy by capitalizing on the resulting relative motion between the blade and a motionless structure or adjacent vibrating blades. The key to optimizing a given damper design is to determine the dynamic weight at which the maximum energy is dissipated without locking the blade at the damper contact point. As the design of turbomachinery blading progresses towards higher-loaded stages with more complex geometry, vibratory modes beyond the primary beam bending become more prominent. This pape will discuss the development of an analytical method to predict damper effectlveness for any blade mode. The analysis is based on a component mode method, and includes provisions for modeling stick-slip at the friction contact. Multiple damper contact points can be evaluated, and the damper design can be blade-to-ground or blade-to-blade with arbitrary phase angle. The results of a series of lab tests with simple beam specimens to evaluate the principal damper design variables will be presented along with the corresponding analytical predictions.
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Via the Defense Technical Information Center (DTIC): Identifier: This paper is part of a conference proceedings. Access a record for the conference proceedings, and possibly a pdf download of the report, at DTIC Via National Technical Report Library: This report may be available for download from NTRL. Use the Title from this record to locate the item in DTIC Online Indications of Public Availability No digital image of an index entry indicating public availability is currently available There has been no verification of an indication of public availability from an inside cover statementRelated report(s)
This report is part of the following conference:
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Proceedings of Damping '91: 13-15 February 1991 San Diego, California (GCA-1 through JCB-17)
WL-TR-91-3078 Volume III