An Inverse Time Marching Method for the Definition of Cascade Geometry

Meauze, G.

doi:10.1115/1.3227328

Cited by 27 publications

(15 citation statements)

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“…The originality of the method consists of calculating the flow field with a permeable blade wall while imposing the Mach number distribution on it. This means that the blade is not modified during the calculation, unlike what is done in the methods of Meauze (1982), Giles andDrela (1987), or Zannetti et al (1984).…”

Section: Inverse Design Methodsmentioning

confidence: 99%

Inverse Design of Compressor and Turbine Blades at Transonic Flow Conditions

Léonard

Braembussche

1992

Volume 1: Turbomachinery

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This paper describes the design of realistic blade shapes using an inverse method. Special attention is given to the geometrical and mechanical constraints imposed upon the blade. Examples presented in this paper illustrate how a better understanding of the theoretical relations between imposed velocity and resulting geometry can help satisfy the geometrical restrictions. Another method using a numerical procedure for finding a compromise between the target velocity distribution and geometrical restrictions is also proposed and illustrated by an example. A blade design procedure using an inviscid inverse method and a boundary layer calculation method is described and applied to the design of a shock free transonic compressor cascade. The iterative character of the procedure provides a blade shape control good enough to design sufficiently thick blades resulting in realistic geometries. The blade shape coordinates are given as a possible bench mark for inviscid or viscous two-dimensional methods.

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Section: Inverse Design Methodsmentioning

confidence: 99%

Inverse Design of Compressor and Turbine Blades at Transonic Flow Conditions

Léonard

Braembussche

1992

Volume 1: Turbomachinery

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“…The effects are implemented by calculating the surface shear stresses and then distributing them to give the components of viscous forces acting on each control volume. The viscous force components are included in the ow formulation as source terms in the right-hand side of each of the momentum equations as shown in equations (1). The surface shear stresses are estimated via a skin friction factor, C f , and distributed via a power law variation.…”

Section: Modelling Of Viscous Effectsmentioning

confidence: 99%

“…Many two-dimensional inverse design methods are available, such as those in references [1] to [3], and are commonly used in the preliminary stage of the design process for axial turbomachines. In recent years, threedimensional inverse design methods have emerged and been applied successfully for a wide range of designs, involving both turbomachinery blades and wings [4][5][6].…”

Section: Introductionmentioning

confidence: 99%

Application of simulated annealing to inverse design of transonic turbomachinery cascades

Tiow

Yiu

Zangeneh

2002

Proceedings of the Institution of Mechanical Engineers, Part A:

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In turbomachinery blade design, inverse methods and optimization techniques are often applied independently to produce high performance blade shapes. The idea of using an optimization algorithm to seek the optimal target distribution for an inverse design methodology has been explored. However, these efforts have been made mainly in the design of single aerofoils. In this paper, a new inverse design method is coupled with a simulated annealing algorithm to search for the optimum turbomachinery cascade shape. In order to speed up the algorithm, a database of generated designs is set up and the nearest match is selected to initialize subsequent calculation. The proposed computational procedure equips engineers with an automatic design tool with which the inverse method may be applied in isolation or combined with the optimization algorithm to produce the optimum.The inverse methodology is based on a cell vertex, nite volume time-marching ow solver that gives the viscous cascade ow solution in both the subsonic and the transonic ow regimes. The cascade shape is computed subject to an imposed distribution of the mass-averaged tangential velocity and a speci ed tangential thickness pro le. The solver code is validated using experimental data and the accuracy of the inverse method is veri ed by regenerating a known cascade geometry starting from a different one using its mass-averaged tangential velocity distribution. In combining the inverse methodology with the optimization algorithm, the mass-averaged tangential velocity distribution is parametrized using a cubic B-spline curve and the proposed simulated annealing algorithm is applied to predict the optimal distribution by minimizing loss. The overall procedure is demonstrated to produce optimum shapes of a transonic axial turbine and an axial compressor rotor.

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“…too thin a profile or in some cases even blades with negative blade thicknesses. Use of a semi-inverse method can eliminate such problems as was demonstrated by Meauze (1981 and1984) by determining the geometry of a blading with a given thickness evolution law and a pressure distribution assigned only on the suction surface. Similarly Dang (1995) proposed a scheme where blade geometry could be generated for prescribed blade loading and thickness distribution.…”

Section: Introductionmentioning

confidence: 99%

A Prescribed Velocity Distribution Scheme for Turbomachine Blading

Singh

1996

Volume 1: Turbomachinery

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The work describes a quasi three dimensional time marching method (Euler Solver), allowing for variations in streamtube height and radius in the meridional plane, for the generation of blade shapes. The method is applicable for both compressor and turbine blades. The generation of the blade shapes is done corresponding to a prescribed pressure distribution (with or without shock waves) around the blade surfaces. The method can be used to either generate entire blade shapes or to modify regions of an existing inefficient blade shape. Viscous effects are allowed for by using an integral boundary layer growth method in the scheme. For the generation of turbine blade shapes the effects of trailing edge base pressure are also included in the method. The accuracy of the scheme has been demonstrated through various test cases. The use of the method results in vast reduction in overall design time and hence cost.

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An Inverse Time Marching Method for the Definition of Cascade Geometry

Cited by 27 publications

References 0 publications

Inverse Design of Compressor and Turbine Blades at Transonic Flow Conditions

Inverse Design of Compressor and Turbine Blades at Transonic Flow Conditions

Application of simulated annealing to inverse design of transonic turbomachinery cascades

A Prescribed Velocity Distribution Scheme for Turbomachine Blading

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