A Design Optimization Procedure for Efficient Turbine Airfoil Design

Chattopadhyay, Aditi; Pagaldipti, N.; Chang, Kuang-Hua

doi:10.1016/0898-1221(93)90031-p

Cited by 15 publications

(4 citation statements)

References 9 publications

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“…Chattopadhyay et al 2 developed an optimisation procedure for designing wind turbine blade section airfoils. It has often been seen that the flow field around the leading edge of airfoils shows velocity spikes.…”

Section: Gradient-based Methodsmentioning

confidence: 99%

Mathematical Modeling, Design, and Optimization of Airfoils and Aircrafts Operating at Specific Reynolds Number

Kakade¹,

Seeni²

2022

ECS Trans.

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Although there are several airfoil designs available to choose from, for the application of aircraft design, the problem of finding the optimal design based on mathematical and physical modeling has not been attempted before. For that purpose, research on existing literature has been done to find the most efficient and optimal airfoil design and optimization technique to be further used for designing and optimizing airfoils. Both physical and mathematical modeling along with other computational algorithms will be used to generate optimal new airfoil designs for high lift and low drag for specific operational conditions.

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Section: Gradient-based Methodsmentioning

confidence: 99%

Mathematical Modeling, Design, and Optimization of Airfoils and Aircrafts Operating at Specific Reynolds Number

Kakade¹,

Seeni²

2022

ECS Trans.

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“…The application of design optimization procedures to turbomachinery blade design has been rather limited. Chattopadhyay et al 7 developed an optimization procedure for efficient design of turbine blades which successfully eliminates the leading edge velocity spikes while maintaining the tangential force coefficient. Aerodynamic analysis was performed using a twodimensional panel code.…”

Section: Introductionmentioning

confidence: 99%

Optimization of turbomachinery airfoil shape for improved performance

Jha

Chattopadhyayt

Rajadas

1998

39th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference and Exhibit

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A new multidisciplinary optimization procedure has been developed for the design of turbine blade profile. Aerodynamic and heat transfer design objectives are integrated along with various mechanical constraints on the blade geometry. The airfoil shape is represented by Bezier-Bernstein polynomials, which results in a relatively small number of design variables for the optimization. Thin shear layer approximation of the Navier-Stokes equation is used for the viscous flow calculations. Grid generation is accomplished by solving Poisson equations. The maximum and average blade temperatures are obtained through a finite element analysis. Total pressure and exit kinetic energy losses are minimized, with constraints on blade temperatures and geometry. The constrained multiobjective optimization problem is solved using the KreisselmeierSteinhauser (K-S) function approach:-The results-for the numerical example show significant improvements after optimization. IntroductionHigh performance aircraft engine components operate under severe aerodynamic, thermal and structural environments. The design of the blade profile is one of the major aspects of engine design 1 . Engine performance is strongly affected by the aerodynamic efficiency of the blades. Higher aerodynamic efficiency can be achieved through efficient design of the blade external shape. Sharp fluctuations in the blade (suction

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“…Airfoil design is optimized by incrementally changing the airfoil shape and evaluating the design at each step [7][8][9]. This approach has been used for several applications, including, wing design [10], airfoil design [11], and supersonic planar nozzle [12] design.…”

Section: Turbine Airfoil Designmentioning

confidence: 99%

Turbine Airfoil Optimization Using Quasi‐3D Analysis Codes

Goel

2009

International Journal of Aerospace Engineering

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A new approach to optimize the geometry of a turbine airfoil by simultaneously designing multiple 2D sections of the airfoil is presented in this paper. The complexity of 3D geometry modeling is circumvented by generating multiple 2D airfoil sections and constraining their geometry in the radial direction using first-and second-order polynomials that ensure smoothness in the radial direction. The flow fields of candidate geometries obtained during optimization are evaluated using a quasi-3D, inviscid, CFD analysis code. An inviscid flow solver is used to reduce the execution time of the analysis. Multiple evaluation criteria based on the Mach number profile obtained from the analysis of each airfoil cross-section are used for computing a quality metric. A key contribution of the paper is the development of metrics that emulate the perception of the human designer in visually evaluating the Mach Number distribution. A mathematical representation of the evaluation criteria coupled with a parametric geometry generator enables the use of formal optimization techniques in the design. The proposed approach is implemented in the optimal design of a low-pressure turbine nozzle.

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A Design Optimization Procedure for Efficient Turbine Airfoil Design

Cited by 15 publications

References 9 publications

Mathematical Modeling, Design, and Optimization of Airfoils and Aircrafts Operating at Specific Reynolds Number

Mathematical Modeling, Design, and Optimization of Airfoils and Aircrafts Operating at Specific Reynolds Number

Optimization of turbomachinery airfoil shape for improved performance

Turbine Airfoil Optimization Using Quasi‐3D Analysis Codes

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