Total pressure loss minimization in turbomachinery cascades using a new continuous adjoint formulation

Papadimitriou, DI; Giannakoglou, KC

dc.contributor.author	Papadimitriou, DI	en
dc.contributor.author	Giannakoglou, KC	en
dc.date.accessioned	2014-03-01T02:44:59Z
dc.date.available	2014-03-01T02:44:59Z
dc.date.issued	2007	en
dc.identifier.issn	0957-6509	en
dc.identifier.uri	https://dspace.lib.ntua.gr/xmlui/handle/123456789/32072
dc.subject	Continuous adjoint approach	en
dc.subject	Shape optimization	en
dc.subject	Turbomachinery	en
dc.subject	Viscous losses minimization	en
dc.subject.classification	Engineering, Mechanical	en
dc.subject.other	Aerodynamics	en
dc.subject.other	Airfoils	en
dc.subject.other	Cascades (fluid mechanics)	en
dc.subject.other	Drag	en
dc.subject.other	Lift	en
dc.subject.other	Pressure distribution	en
dc.subject.other	Shape optimization	en
dc.subject.other	Continuous adjoint approach	en
dc.subject.other	Objective function gradient	en
dc.subject.other	Pressure loss	en
dc.subject.other	Turbomachinery	en
dc.subject.other	Aerodynamics	en
dc.subject.other	Airfoils	en
dc.subject.other	Cascades (fluid mechanics)	en
dc.subject.other	Drag	en
dc.subject.other	Lift	en
dc.subject.other	Pressure distribution	en
dc.subject.other	Shape optimization	en
dc.subject.other	Turbomachinery	en
dc.title	Total pressure loss minimization in turbomachinery cascades using a new continuous adjoint formulation	en
heal.type	conferenceItem	en
heal.identifier.primary	10.1243/09576509JPE463	en
heal.identifier.secondary	http://dx.doi.org/10.1243/09576509JPE463	en
heal.language	English	en
heal.publicationDate	2007	en
heal.abstract	A new continuous adjoint formulation for the optimization of cascade aerofoils with minimum total pressure losses, i.e. an objective function which has never been used before along with the continuous adjoint, is presented. To support a steepest descent algorithm, the adjoint method is used to compute the gradient of the objective function with respect to the design variables. The function is defined as the difference in total pressure between the inlet to and the outlet from the cascade. In contrast to other known continuous adjoint approaches in aerodynamics (such as inverse designs based on target pressure distributions or drag-lift optimization for isolated aerofoils), where the functional is defined over the parameterized solid walls, the present functional consists of integrals over the inlet/outlet boundaries only. To cope with this particular situation, the method of characteristics is used to impose inlet/outlet adjoint boundary conditions. It is worth noting that the objective function gradient is expressed as an integral over the solid walls. The minimization of losses in linear and peripheral compressor cascades, constrained by the desirable flow turning and the minimum allowed blade thickness, are demonstrated. © IMechE 2007.	en
heal.publisher	PROFESSIONAL ENGINEERING PUBLISHING LTD	en
heal.journalName	Proceedings of the Institution of Mechanical Engineers, Part A: Journal of Power and Energy	en
dc.identifier.doi	10.1243/09576509JPE463	en
dc.identifier.isi	ISI:000250435800014	en
dc.identifier.volume	221	en
dc.identifier.issue	6	en
dc.identifier.spage	865	en
dc.identifier.epage	872	en