The Use of Optimization Techniques to Design Controlled Diffusion Compressor Blading

Sanger, N. L.

doi:10.1115/82-gt-149

Cited by 19 publications

(12 citation statements)

References 2 publications

(1 reference statement)

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“…Keskin and Bestle [39] reported Bezier curve parameterization of blade shape to optimize with Pareto optimal design. Optimization of controlled diffusion compressor blade has been reported by Sanger [82].…”

Section: Applications Of Surrogate Based Optimization Methodsmentioning

confidence: 99%

Surrogate Based Optimization Techniques for Aerodynamic Design of Turbomachinery

Samad¹,

Kim²

2009

International Journal of Fluid Machinery and Systems

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Recent development of high speed computers and use of optimization techniques have given a big momentum of turbomachinery design replacing expensive experimental cost as well as trial and error approaches. The surrogate based optimization techniques being used for aerodynamic turbomachinery designs coupled with Reynolds-averaged NavierStokes equations analysis involve single-and multi-objective optimization methods. The objectives commonly tried to improve were adiabatic efficiency, pressure ratio, weight etc. Presently coupling the fluid flow and structural analysis is being tried to find better design in terms of weight, flutter and vibration, and turbine life. The present article reviews the surrogate based optimization techniques used recently in turbomachinery shape optimizations.

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Section: Applications Of Surrogate Based Optimization Methodsmentioning

confidence: 99%

Surrogate Based Optimization Techniques for Aerodynamic Design of Turbomachinery

Samad¹,

Kim²

2009

International Journal of Fluid Machinery and Systems

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“…The simulations presented here are performed on a geometry that is restricted to an idealised, highly-loaded compressor blade [17] at a Reynolds number of ∼ 700,000 based on chord length and inlet velocity V i . Many numerical studies on this compressor have been performed but to date the cascade has not been the subject of a systematic study using Large Eddy Simulation.…”

Section: Introductionmentioning

confidence: 99%

Large Eddy Simulation of a Controlled Diffusion Compressor Cascade

McMullan

Page

2010

Flow Turbulence Combust

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In this research a Controlled Diffusion (CD) compressor cascade stator blade is simulated at a Reynolds number of ∼ 700, 000, based on inflow velocity and chord length, using Large Eddy Simulation (LES). A wide range of flow inlet angles are computed, including conditions near the design angle, and at high negative and positive incidence. At all inlet angles the surface pressure distributions are well-predicted by the LES. Near the design angle the computed suction side boundary layer thickness agrees well with experimental data, whilst the pressure side boundary layer is poorly predicted due to the inability of LES to capture natural boundary layer transition on the present grid. A good estimation of the loss is computed near the design angle, whilst at both high positive and negative incidences the loss is less well predicted owing to discrepancies between the computed and experimental boundary layer thickness. At incidences above the design angle a laminar separation bubble forms near the leading edge of the suction surface, which undergoes a transition to turbulence. Similar behaviour is noted on the pressure surface at negative incidence. At high negative incidence contra-rotating vortex pairs are found to form around the leading edge inThe authors would like to thank Rolls-Royce plc and the UK Technology Strategy Board for the funding this work under the CFMS Core Programme (TP/L3001H). The simulations in this study were performed on HECToR, the UK National Supercomputing Facility, under the UKAAC-2 Framework, EPSRC grant number EP/F005954/1. response to an unsteady stagnation line across the span of the blade. Such structures are not apparent in time-averaged statistical data due to their highly-transient nature.

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“…Instead of specifying the ultimate goal, as in inverse design, a search methodology is provided. CFD based optimization is capable of modifying a geometry in order to improve a design while remaining within specified design constraints 4,5 . In this manner, a specific design parameter may be improved without the degradation of other aspects of the design.…”

Section: Introductionmentioning

confidence: 99%

Turbomachinery blade optimization using the Navier-Stokes equations

Chang

Lee

1998

36th AIAA Aerospace Sciences Meeting and Exhibit

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December 1997This is a preprint of a paper intended for publication in a journal or proceedings. Since changes may be made before publication, this preprint is made available with the understanding that it will not be cited or reproduced without the permission of the author. A method is presented to perform aerodynamic design optimization of turbomachinery blades. The method couples a Navier-Stokes flow solver with a grid generator and numerical optimization algorithm to seek improved designs for transonic turbine blades. A fast and efficient multigrid, finite-volume flow solver provides accurate performance evaluations of potential designs. Design variables consist of smooth perturbations to the blade surface. A unique elliptic-hyperbolic grid generation method is used to regenerate a Navier-Stokes grid after perturbations have been added to the geometry. Designs are sought which improve a design objective while remaining within specified constraints. The method is demonstrated with two transonic turbine blades with different types and numbers of design variables. PREPRINT

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The Use of Optimization Techniques to Design Controlled Diffusion Compressor Blading

Cited by 19 publications

References 2 publications

Surrogate Based Optimization Techniques for Aerodynamic Design of Turbomachinery

Surrogate Based Optimization Techniques for Aerodynamic Design of Turbomachinery

Large Eddy Simulation of a Controlled Diffusion Compressor Cascade

Turbomachinery blade optimization using the Navier-Stokes equations

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