Abstract
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 language | English (US) |
|---|---|
| Pages (from-to) | 1850-1863 |
| Number of pages | 14 |
| Journal | Collection of Technical Papers - AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference |
| Volume | 3 |
| DOIs | |
| State | Published - 2002 |
| Event | 43rd Structures, Structural Dynamics and Materials Conference - Denver, CO, United States Duration: Apr 22 2002 → Apr 25 2002 |
All Science Journal Classification (ASJC) codes
- Architecture
- General Materials Science
- Aerospace Engineering
- Mechanics of Materials
- Mechanical Engineering