Refined structural modeling and structural dynamics of elastically tailored composite rotor blades

Louis R. Centolanza, Edward Smith, Benoy Kumar

Research output: Contribution to conferencePaper

4 Citations (Scopus)

Abstract

A refined analytical model based on Vlasov theory is developed to (1) predict the cross-sectional stiffness constants for thin walled multi-cell composite rotor blades, (2) determine the location of the shear center for thin walled multicell composite rotor blade crosssections, and (3) investigate the effects of using spanwise non-uniform lay-ups to produce a desired twist distribution. The model uses an expanded Vlasov theory that includes transverse shear deformation of the cross-section, a warping function that captures the variation of shear stiffness along the contour of the cross-section, and the effect of two-dimensional ply elasticity. Analytical results are validated with both experimental data and detailed finite element results. The effects of ignoring two dimensional inplane ply elasticity, inplane warping, and local bending moments and curvatures were investigated using the new structural model. The influence of the skin and web thickness on the shear center location and torsion rigidity was also studied. The results show that the ignoring the two-dimensional inplane ply elasticity has a significant effect on the cross-sectional stiffness. Neglecting the local shell bending moments and twists has a significant effect on torsional rigidity for relatively thicker walled cross-sections. It was found that in-plane warping is not important for thin walled closed cell cross-sections. The shear center position is ' insensitive to the airfoil skin thickness but is sensitive to the web thickness. Torsional rigidity is influenced by the airfoil skin thickness but not influenced by the web thickness for relatively thick skin airfoils. The cross-sectional model was also integrated with a structural dynamic analysis of composite rotor blades. By using spanwise uniform and non-uniform ply-layups, a preliminary investigation on the behnvior of the composite blades was conducted. The results reveal that mode shapes are sensitive to the spanwise lay-up, however, natural frequencies remain essentially unchanged.

Original languageEnglish (US)
Pages2002-2012
Number of pages11
DOIs
StatePublished - Jan 1 1996
Event37th AIAA/ASME/ASCE/AHS/ASC Structure, Structural Dynamics and Materials Conference, 1996 - Salt Lake City, United States
Duration: Apr 15 1996Apr 17 1996

Other

Other37th AIAA/ASME/ASCE/AHS/ASC Structure, Structural Dynamics and Materials Conference, 1996
CountryUnited States
CitySalt Lake City
Period4/15/964/17/96

Fingerprint

Structural dynamics
Turbomachine blades
Skin
Rotors
Airfoils
Rigidity
Elasticity
Stiffness
Composite materials
Bending moments
Torsional stress
Dynamic analysis
Shear deformation
Analytical models
Natural frequencies

All Science Journal Classification (ASJC) codes

  • Civil and Structural Engineering
  • Mechanics of Materials
  • Architecture
  • Building and Construction

Cite this

Centolanza, L. R., Smith, E., & Kumar, B. (1996). Refined structural modeling and structural dynamics of elastically tailored composite rotor blades. 2002-2012. Paper presented at 37th AIAA/ASME/ASCE/AHS/ASC Structure, Structural Dynamics and Materials Conference, 1996, Salt Lake City, United States. https://doi.org/10.2514/6.1996-1549
Centolanza, Louis R. ; Smith, Edward ; Kumar, Benoy. / Refined structural modeling and structural dynamics of elastically tailored composite rotor blades. Paper presented at 37th AIAA/ASME/ASCE/AHS/ASC Structure, Structural Dynamics and Materials Conference, 1996, Salt Lake City, United States.11 p.
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Centolanza, LR, Smith, E & Kumar, B 1996, 'Refined structural modeling and structural dynamics of elastically tailored composite rotor blades' Paper presented at 37th AIAA/ASME/ASCE/AHS/ASC Structure, Structural Dynamics and Materials Conference, 1996, Salt Lake City, United States, 4/15/96 - 4/17/96, pp. 2002-2012. https://doi.org/10.2514/6.1996-1549

Refined structural modeling and structural dynamics of elastically tailored composite rotor blades. / Centolanza, Louis R.; Smith, Edward; Kumar, Benoy.

1996. 2002-2012 Paper presented at 37th AIAA/ASME/ASCE/AHS/ASC Structure, Structural Dynamics and Materials Conference, 1996, Salt Lake City, United States.

Research output: Contribution to conferencePaper

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N2 - A refined analytical model based on Vlasov theory is developed to (1) predict the cross-sectional stiffness constants for thin walled multi-cell composite rotor blades, (2) determine the location of the shear center for thin walled multicell composite rotor blade crosssections, and (3) investigate the effects of using spanwise non-uniform lay-ups to produce a desired twist distribution. The model uses an expanded Vlasov theory that includes transverse shear deformation of the cross-section, a warping function that captures the variation of shear stiffness along the contour of the cross-section, and the effect of two-dimensional ply elasticity. Analytical results are validated with both experimental data and detailed finite element results. The effects of ignoring two dimensional inplane ply elasticity, inplane warping, and local bending moments and curvatures were investigated using the new structural model. The influence of the skin and web thickness on the shear center location and torsion rigidity was also studied. The results show that the ignoring the two-dimensional inplane ply elasticity has a significant effect on the cross-sectional stiffness. Neglecting the local shell bending moments and twists has a significant effect on torsional rigidity for relatively thicker walled cross-sections. It was found that in-plane warping is not important for thin walled closed cell cross-sections. The shear center position is ' insensitive to the airfoil skin thickness but is sensitive to the web thickness. Torsional rigidity is influenced by the airfoil skin thickness but not influenced by the web thickness for relatively thick skin airfoils. The cross-sectional model was also integrated with a structural dynamic analysis of composite rotor blades. By using spanwise uniform and non-uniform ply-layups, a preliminary investigation on the behnvior of the composite blades was conducted. The results reveal that mode shapes are sensitive to the spanwise lay-up, however, natural frequencies remain essentially unchanged.

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Centolanza LR, Smith E, Kumar B. Refined structural modeling and structural dynamics of elastically tailored composite rotor blades. 1996. Paper presented at 37th AIAA/ASME/ASCE/AHS/ASC Structure, Structural Dynamics and Materials Conference, 1996, Salt Lake City, United States. https://doi.org/10.2514/6.1996-1549