Reduced-Order Aerodynamic Models For Analysis of Mistuned Bladed Disks

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Reduced-Order Aerodynamic Models For Analysis of
Mistuned Bladed Disks

Tan Bui, Prof. Karen Willcox

• Motivation
• Mistuning is when the blades in a compressor or
  turbine of an engine are not quite identical,
  e.g. because of random manufacturing variation,
  or wear and tear. This asymmetry can cause a
  significant increase in the resonant amplitude
  for some of the blades, leading to a critical
  phenomenon called high cycle fatigue (HCF). HCF
  can cause major problems in gas turbine engines.
• Goals
• Formulate, implement and demonstrate a coupled
  aerodynamic/structural framework for analysis of
  mistuned bladed disks.
• Reduced-order aerodynamic models will be created
  from a high-order CFD code and coupled with an
  existing structural mistuning framework.
• Investigate the effects of aerodynamic damping on
  aeroelastic behavior of mistuned bladed disks and
  quantify the impact on aerodynamic performance of
  intentional mistuning.

Funded by Dr. James Kenyon, AFRL. Collaboration
with Dr. Feiner and Prof. Griffin, CMU.
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Methodology
Blade forces
Finite Element Structural model

• Discontinuous Galerkin Aerodynamic CFD Model

Blade displacements
Proper Orthogonal Decomposition
Fundamental Mistuning Model
Blade forces
Low Order Structural model
Low Order Aerodynamic Model
Blade displacements
Low Order Aeroelastic model
INVESTIGATE AERODYNAMIC EFFECTS FOR MISTUNED
BLADED DISKS