The effects of embedded chordwise absorbers on blade aeroelastic stability

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3 Scopus citations


The effects of a unique chordwise absorber on blade aeroelastic stability are investigated. The primary goal of this device is to augment blade lag damping. Analytical models of blade-absorber system are developed using a rigid blade-absorber model and an elastic blade-absorber model, respectively. The chordwise absorber is modeled using a mass-spring pair and assumed to move in the chordwise direction of the blade. In the rigid blade modeling, the blade is idealized as a rigid beam undergoing flap, lag, and feathering rotations about three hinges. In the elastic blade modeling, the blade is modeled as a slender elastic beam undergoing flap bending, lag bending, and elastic twist. A quasi-steady blade element aerodynamic model is used to calculate the airloads of the blade. Qualitative analysis and initial quantitative analysis is first conducted using the rigid blade-absorber model. Detailed numerical analysis is then performed using the elastic blade-absorber model. The results show that chordwise absorber has a considerable influence on blade aeroelastic stability. For soft inplane blade, 0.1% to 0.25% critical damping augmentation for blade lag mode can be obtained using the embedded chordwise absorber. For stiff inplane rotor blade, blade lag damping augmentation varies from 1% to 3% critical damping depending on absorber parameters.

Original languageEnglish (US)
Pages (from-to)1850-1863
Number of pages14
JournalCollection of Technical Papers - AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference
StatePublished - 2002
Event43rd Structures, Structural Dynamics and Materials Conference - Denver, CO, United States
Duration: Apr 22 2002Apr 25 2002

All Science Journal Classification (ASJC) codes

  • Architecture
  • General Materials Science
  • Aerospace Engineering
  • Mechanics of Materials
  • Mechanical Engineering


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