Axial compressor stage analysis through a multi-block 3-D Navier-Stokes solution method

Politis, ES; Giannakoglou, KC; Papailiou, KD

dc.contributor.author	Politis, ES	en
dc.contributor.author	Giannakoglou, KC	en
dc.contributor.author	Papailiou, KD	en
dc.date.accessioned	2014-03-01T02:48:30Z
dc.date.available	2014-03-01T02:48:30Z
dc.date.issued	1997	en
dc.identifier.issn	04021215	en
dc.identifier.uri	https://dspace.lib.ntua.gr/xmlui/handle/123456789/33868
dc.relation.uri	http://www.scopus.com/inward/record.url?eid=2-s2.0-0031340618&partnerID=40&md5=8eb1c5df7921222804a22db7d883084b	en
dc.subject.other	Axial flow turbomachinery	en
dc.subject.other	Compressors	en
dc.subject.other	Computer software	en
dc.subject.other	Convergence of numerical methods	en
dc.subject.other	Mathematical models	en
dc.subject.other	Matrix algebra	en
dc.subject.other	Navier Stokes equations	en
dc.subject.other	Rotors	en
dc.subject.other	Stators	en
dc.subject.other	Turbomachine blades	en
dc.subject.other	Wall flow	en
dc.subject.other	Generalized residual minimization scheme	en
dc.subject.other	Computational fluid dynamics	en
dc.title	Axial compressor stage analysis through a multi-block 3-D Navier-Stokes solution method	en
heal.type	conferenceItem	en
heal.publicationDate	1997	en
heal.abstract	A method for the analysis of low-speed flows in compressor stages through a steady, 3-D, multi-block, Navier-Stokes solver is presented. For a complete stage, two pairs of 3-D grid blocks, one for the rotor and one for the stator, are used. The combination of two grids per row aims at the accurate modelling of the flow in the clearances between blade tips of finite thickness and annular walls. Thus, with such a numerical tool, the effect of rotor tip-clearance on the downstream stator performance, can be studied. Within each grid block, governing equations are solved in a segregated manner through the inversion of a single scalar coefficient matrix for all but the continuity equation. For the latter, a pressure correction equation is solved using a generalized residual minimization scheme. The interfaces between rows are treated through a simple mixing approach, based on the communication of circumferentially area-averaged quantities. The interfaces between grid blocks in the same row are treated by means of fake cells. Both interfacing schemes do not badly affect the convergence of the code. The method is used for the analysis of the third stage of a four-stage, low-speed compressor, for which unsteady flow phenomena do not dominate the physics of the flow. Numerical predictions are compared to data from experimental work carried out at the Cranfield University test rig.	en
heal.publisher	ASME, New York, NY, United States	en
heal.journalName	American Society of Mechanical Engineers (Paper)	en