Compressor blade optimization using a continuous adjoint formulation

Papadimitriou, DI; Giannakoglou, KC

dc.contributor.author	Papadimitriou, DI	en
dc.contributor.author	Giannakoglou, KC	en
dc.date.accessioned	2014-03-01T02:43:59Z
dc.date.available	2014-03-01T02:43:59Z
dc.date.issued	2006	en
dc.identifier.uri	https://dspace.lib.ntua.gr/xmlui/handle/123456789/31590
dc.relation.uri	http://www.scopus.com/inward/record.url?eid=2-s2.0-33750874487&partnerID=40&md5=bc4b40605574228281c684c5e15f249f	en
dc.relation.uri	http://147.102.55.162/research/pdfs/3_081.pdf	en
dc.subject	Adjoint Method	en
dc.subject	Constrained Optimization	en
dc.subject	Entropy Generation	en
dc.subject	Geometric Constraints	en
dc.subject	lagrange multiplier	en
dc.subject	Objective Function	en
dc.subject	Penalty Method	en
dc.subject	navier-stokes equation	en
dc.subject	Non Uniform Rational B Spline	en
dc.subject	Steepest Descent	en
dc.subject.other	Cascade efficiency	en
dc.subject.other	Compressor blade cascade	en
dc.subject.other	Design variables	en
dc.subject.other	Objective function	en
dc.subject.other	Aerodynamics	en
dc.subject.other	Cascades (fluid mechanics)	en
dc.subject.other	Compressors	en
dc.subject.other	Gradient methods	en
dc.subject.other	Navier Stokes equations	en
dc.subject.other	Splines	en
dc.subject.other	Turbomachine blades	en
dc.title	Compressor blade optimization using a continuous adjoint formulation	en
heal.type	conferenceItem	en
heal.publicationDate	2006	en
heal.abstract	In this paper, a constrained optimization algorithm is formulated and utilized to improve the aerodynamic performance of a 3D peripheral compressor blade cascade. The cascade efficiency is measured in terms of entropy generation along the developed flowfield, which defines the field objective functional to be minimized. Its gradient with respect to the design variables, which are the coordinates of the Non-Uniform Rational B-Spline (NURBS) control points defining the blade, is computed through a continuous adjoint formulation of the Navier-Stokes equations based on the aforementioned functional. The steepest descent algorithm is used to locate the optimal set of design variables, i.e. the optimal blade shape. In addition to the well-known advantages of the adjoint method, the current formulation has even less CPU cost for the gradient computation as it leads to gradient expression which is free of field variations in geometrical quantities (such as derivatives of interior grid node coordinates with respect to the design variables); the computation of the latter would be costly since it requires remeshing anew the computational domain for each bifurcated design variable. The geometrical constraints, which depend solely on the blade parameterization, are handled by a quadratic penalty method by introducing additional Lagrange multipliers. Copyright © 2006 by ASME.	en
heal.journalName	Proceedings of the ASME Turbo Expo	en
dc.identifier.volume	6 PART B	en
dc.identifier.spage	1309	en
dc.identifier.epage	1317	en