Aerodynamic inverse design of turbomachinery cascades using a finite volume method on unstructured meshes

Ahmadi, Majid; Ghaly, Wahid

doi:10.1080/174159798088027680

Cited by 6 publications

(3 citation statements)

References 11 publications

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“…Note that the optimal design has a reversed curvature particularly along the suction side to allow the flow to compress reversibly. Other researchers (Ahmadi and Ghaly 1998;Dang 1995) have also observed similar behavior.…”

Section: Redesign Of a Transonic Impulse Turbine Cascadesupporting

confidence: 61%

Aerodynamic optimization of turbomachinery blades using evolutionary methods and ANN-based surrogate models

Mengistu

Ghaly

2007

Optim Eng

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A fast, flexible, and robust simulation-based optimization scheme using an ANN-surrogate model was developed, implemented, and validated. The optimization method uses Genetic Algorithm (GA), which is coupled with an Artificial Neural Network (ANN) that uses a back propagation algorithm. The developed optimization scheme was successfully applied to single-point aerodynamic optimization of a transonic turbine stator and multi-point optimization of a NACA65 subsonic compressor rotor in two-dimensional flow, both were represented by 2D linear cascades. High fidelity CFD flow simulations, which solve the Reynolds-Averaged Navier-Stokes equations, were used in generating the data base used in building the ANN low fidelity model. The optimization objective is a weighted sum of the performance objectives and is penalized with the constraints; it was constructed so as to achieve a better aerodynamic performance at the design point or over the full operating range by reshaping the blade profile. The latter is represented using NURBS functions, whose coefficients are used as the design variables. Parallelizing the CFD flow simulations reduced the turn-around computation time at close to 100% efficiency. The ANN model was able to approximate the objective function rather accurately and to reduce the optimization computing time by ten folds. The chosen objective function and optimization methodology result in a significant and consistent improvement in blade performance.

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Section: Redesign Of a Transonic Impulse Turbine Cascadesupporting

confidence: 61%

Aerodynamic optimization of turbomachinery blades using evolutionary methods and ANN-based surrogate models

Mengistu

Ghaly

2007

Optim Eng

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“…In 2D cascades, performance is defined by the design specification of either the flow properties on one or both sides of the blade, typically pressure, velocity or Mach number distribution (Lighthill, 1945;Giles & Drela, 1987;Leonard & Van Den Braembussche, 1992). A noticeable application of inverse methods for the design of transonic compressor cascade is given by Ahmadi, 1998, who implemented a cell-vertex finite volume method on unstructured triangular meshes. In this design method, the mass-averaged swirl schedule and the blade thickness distribution were prescribed.…”

Section: Inverse Methodsmentioning

confidence: 99%

Advances in Aerodynamic Design of Gas Turbines Compressors

Benini¹

2010

Gas Turbines

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“…Furthermore, the DP speci cation can be readily used in three dimensions. The initial development of this methodology in two dimensions was covered in earlier work [14] and separately in references [15] and [16]. More recent applications of this method are reported in references [17] and [18].…”

Section: Introductionmentioning

confidence: 99%

Application of a three-dimensional viscous transonic inverse method to NASA rotor 67

Tiow

Zangeneh

2002

Proceedings of the Institution of Mechanical Engineers, Part A:

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The development and application of a three-dimensional inverse methodology in which the blade geometry is computed on the basis of the speci cation of static pressure loading distribution is presented. The methodology is based on the intensive use of computational uid dynamics (CFD) to account for three-dimensional subsonic and transonic viscous ows. In the design computation, the necessary blade changes are determined directly by the discrepancies between the target and initial values, and the calculation converges to give the nal blade geometry and the corresponding steady state ow solution. The application of the method is explored using a transonic test case, NASA rotor 67. Based on observations, it is conclusive that the shock formation and its intensity in such a high-speed turbomachinery ow are well de ned on the loading distributions. Pressure loading is therefore as effective a design parameter as conventional inverse design quantities such as static pressure. Hence, from an understanding of the dynamics of the ow in the fan in relation to its pressure loading distributions, simple guidelines can be developed for the inverse method in order to weaken the shock formation. A qualitative improvement in performance is achieved in the redesigned fan. The nal ow eld result is con rmed by a well-established commercial CFD package.

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Aerodynamic inverse design of turbomachinery cascades using a finite volume method on unstructured meshes

Cited by 6 publications

References 11 publications

Aerodynamic optimization of turbomachinery blades using evolutionary methods and ANN-based surrogate models

Aerodynamic optimization of turbomachinery blades using evolutionary methods and ANN-based surrogate models

Advances in Aerodynamic Design of Gas Turbines Compressors

Application of a three-dimensional viscous transonic inverse method to NASA rotor 67

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