Pre-Deformation Method for Manufactured Compressor Blade Based on Load Incremental Approach
-
Kang Da
,
Wang Yongliang
Abstract
The blade deformation caused by aerodynamic and centrifugal loads during operating makes blade configurations different from their stationary shape. Based on the load incremental approach, a novel pre-deformation method for cold blade shape is provided in order to compensate blade deformation under running. Effect of nonlinear blade stiffness is considered by updating stiffness matrix in response to the variation of blade configuration when calculating deformations. The pre-deformation procedure is iterated till a converged cold blade shape is obtained. The proposed pre-deformation method is applied to a transonic compressor rotor. Effect of load conditions on blade pre-deformation is also analyzed. The results show that the pre-deformation method is easy to implement with fast convergence speed. Neither the aerodynamic load nor centrifugal load can be neglected in blade pre-deformation.
Funding statement: This investigation was supported by National Natural Science Foundation of China (Grant No. 51606023 and 51436002), Natural Science Foundation of Liaoning Province, (Grant No. 2015020130), and Fundamental Research Funds for the Central Universities, (Grant No. 3132017015).
Nomenclature
- F
Load force
- U
Structural displacement
Load increment
Displacement increment
Stiffness matrix
- m
The number of load segments
- X
Node coordinates
Criteria for residual
- AL
Aerodynamic load
- CL
Centrifugal load
- CFD
Computational fluid dynamics
- CSD
Computational structural dynamics
- Subscript
- i
Iteration
- Superscript
- Hot
Hot blade
- Cold
Cold blade
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Articles in the same Issue
- Frontmatter
- Original Research Articles
- Investigation on Rotor-Labyrinth Seal System with Variable Rotating Speed
- Numerical Study on the Secondary Air Performance of the Film Holes for the Combined Impingement and Film Cooled First Stage of High Pressure Gas Turbine Nozzle Guide Vane
- Application and Design of Multi-Impingement Cooling Channel in Turbine Blade Trail Edge
- Pre-Deformation Method for Manufactured Compressor Blade Based on Load Incremental Approach
- Control of Supersonic Elliptic Jet with Ventilated Tabs
- Ceramic Matrix Composite Turbine Vane Thermal Simulation Test and Evaluation
- Investigation on Performance of Compressor Cascade with Tubercle Leading Edge Blade
- Numerical Study on Thermal Choke Behaviors Driven by Various Rocket Operations in an RBCC Engine in Ramjet Mode
Articles in the same Issue
- Frontmatter
- Original Research Articles
- Investigation on Rotor-Labyrinth Seal System with Variable Rotating Speed
- Numerical Study on the Secondary Air Performance of the Film Holes for the Combined Impingement and Film Cooled First Stage of High Pressure Gas Turbine Nozzle Guide Vane
- Application and Design of Multi-Impingement Cooling Channel in Turbine Blade Trail Edge
- Pre-Deformation Method for Manufactured Compressor Blade Based on Load Incremental Approach
- Control of Supersonic Elliptic Jet with Ventilated Tabs
- Ceramic Matrix Composite Turbine Vane Thermal Simulation Test and Evaluation
- Investigation on Performance of Compressor Cascade with Tubercle Leading Edge Blade
- Numerical Study on Thermal Choke Behaviors Driven by Various Rocket Operations in an RBCC Engine in Ramjet Mode
