Rotor Balancing with Turbine Blade Assembly Using Ant Colony Optimization for Aero-Engine Applications
-
Altug Piskin
and
Tolga Baklacioglu
Abstract
The purpose of this paper is to present a novel turbine balancing using Ant Colony Optimization method. Results are compared against well known optimization methods available at open literature. With the new approach, turbine blade set can be separated in to two blade sets as heavy and light blades. This approach makes possible the application of Ant Colony Optimization methodology. ACO methodology is compared with Steepest Descent and Exchange Heuristic methods using nine different initial blade placements. And results are presented. Performance of the three evaluated methods is affected by the initial blade placement. Exchange Heuristics method was quick and provided good results in most of the cases. Ant colony optimization was able find better results than the Steepest Descent method. The approach of separating blades into two sets decreased the solution time of Steepest Descent algorithm. Ant colony optimization method can be used for turbine blade assembly and balancing for aircraft gas turbine applications. This approach is used for the first time in this area and not seen at the open literature.
Nomenclature
- B1
Set of position numbers of the heavy blades
- B2
Set of position numbers of the light blades
- d
Deviation of the center of gravity, m
- r
Radius, m
- x
position vector of center of gravity for single blade
- X
position vector of center of gravity for total weight
- w
weight of single blade
- W
total weight of system
- S
set of blades
- Greek Letters
- ϴ
Blade position angle, °
- Subscripts and superscripts
- i
Blade number
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© 2017 Walter de Gruyter GmbH, Berlin/Boston
Articles in the same Issue
- Frontmatter
- Rotor Balancing with Turbine Blade Assembly Using Ant Colony Optimization for Aero-Engine Applications
- Effect of Thermal Conductivity on Nozzle Guide Vane Internal Surface Temperature Distribution
- Investigation of Leading Edge Tubercles with Different Wavelengths in an Annular Compressor Cascade
- Risk Analysis of Propulsion System based on Similarity Measure and Weighted Fuzzy Risk Priority Number in FMEA
- Research on Integrated Control Method of Tiltrotor with Variable Rotor Speed Based on Two-Speed Gearbox
- Thermo-Efficiencies of a Tubular Combustor Under Different Inlet Conditions
- Flow Mixing and Screech Characteristics of Elliptical Supersonic Jet
- Numerical Simulation on the Effect of Cooling Hole Configuration on the Film Cooling Effectiveness in TBC Coated Turbine Vanes
- An Investigation of the Behavior of Steady-State Laminar Jet Spray Flames
Articles in the same Issue
- Frontmatter
- Rotor Balancing with Turbine Blade Assembly Using Ant Colony Optimization for Aero-Engine Applications
- Effect of Thermal Conductivity on Nozzle Guide Vane Internal Surface Temperature Distribution
- Investigation of Leading Edge Tubercles with Different Wavelengths in an Annular Compressor Cascade
- Risk Analysis of Propulsion System based on Similarity Measure and Weighted Fuzzy Risk Priority Number in FMEA
- Research on Integrated Control Method of Tiltrotor with Variable Rotor Speed Based on Two-Speed Gearbox
- Thermo-Efficiencies of a Tubular Combustor Under Different Inlet Conditions
- Flow Mixing and Screech Characteristics of Elliptical Supersonic Jet
- Numerical Simulation on the Effect of Cooling Hole Configuration on the Film Cooling Effectiveness in TBC Coated Turbine Vanes
- An Investigation of the Behavior of Steady-State Laminar Jet Spray Flames
