The effects of embedded chordwise absorbers on blade aeroelastic stability

Research output: Contribution to journalConference article

3 Citations (Scopus)

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 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
Volume3
StatePublished - Jan 1 2002
Event43rd Structures, Structural Dynamics and Materials Conference - Denver, CO, United States
Duration: Apr 22 2002Apr 25 2002

Fingerprint

Damping
Turbomachine blades
Hinges
Numerical analysis
Analytical models
Aerodynamics
Rotors
Chemical analysis

All Science Journal Classification (ASJC) codes

  • Architecture
  • Materials Science(all)
  • Aerospace Engineering
  • Mechanics of Materials
  • Mechanical Engineering

Cite this

@article{3375905b4a8248b1ad154b9cfecf7ba2,
title = "The effects of embedded chordwise absorbers on blade aeroelastic stability",
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.",
author = "Hao Kang and Edward Smith and Lesieutre, {George A.}",
year = "2002",
month = "1",
day = "1",
language = "English (US)",
volume = "3",
pages = "1850--1863",
journal = "Collection of Technical Papers - AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference",
issn = "0273-4508",
publisher = "American Institute of Aeronautics and Astronautics Inc. (AIAA)",

}

TY - JOUR

T1 - The effects of embedded chordwise absorbers on blade aeroelastic stability

AU - Kang, Hao

AU - Smith, Edward

AU - Lesieutre, George A.

PY - 2002/1/1

Y1 - 2002/1/1

N2 - 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.

AB - 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.

UR - http://www.scopus.com/inward/record.url?scp=0036078959&partnerID=8YFLogxK

UR - http://www.scopus.com/inward/citedby.url?scp=0036078959&partnerID=8YFLogxK

M3 - Conference article

VL - 3

SP - 1850

EP - 1863

JO - Collection of Technical Papers - AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference

JF - Collection of Technical Papers - AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference

SN - 0273-4508

ER -