Study of radial tip clearance effects in a low-speed axial compressor rotor

Nikolaou, IG; Giannakoglou, KC; Papailiou, KD

dc.contributor.author	Nikolaou, IG	en
dc.contributor.author	Giannakoglou, KC	en
dc.contributor.author	Papailiou, KD	en
dc.date.accessioned	2014-03-01T02:48:27Z
dc.date.available	2014-03-01T02:48:27Z
dc.date.issued	1996	en
dc.identifier.issn	04021215	en
dc.identifier.uri	https://dspace.lib.ntua.gr/xmlui/handle/123456789/33812
dc.relation.uri	http://www.scopus.com/inward/record.url?eid=2-s2.0-0029719249&partnerID=40&md5=bb1cf6b6dd0117c88e8b3d4620d682ca	en
dc.subject.other	Axial flow	en
dc.subject.other	Axial flow turbomachinery	en
dc.subject.other	Codes (symbols)	en
dc.subject.other	Compressors	en
dc.subject.other	Computer simulation	en
dc.subject.other	Computer software	en
dc.subject.other	Energy dissipation	en
dc.subject.other	Flow patterns	en
dc.subject.other	Geometry	en
dc.subject.other	Mathematical models	en
dc.subject.other	Navier Stokes equations	en
dc.subject.other	Three dimensional	en
dc.subject.other	Cartesian coordinates	en
dc.subject.other	Low speed axial compressor rotor	en
dc.subject.other	Main passage flow	en
dc.subject.other	Pressure loss coefficient	en
dc.subject.other	Radial tip clearance effects	en
dc.subject.other	Rotor geometry	en
dc.subject.other	Three dimensional space marching code	en
dc.subject.other	Tip leakage impact	en
dc.subject.other	Turbulent kinetic energy	en
dc.subject.other	Turbulent viscosity	en
dc.subject.other	Rotors	en
dc.title	Study of radial tip clearance effects in a low-speed axial compressor rotor	en
heal.type	conferenceItem	en
heal.publicationDate	1996	en
heal.abstract	A three-dimensional space marching code is used for the numerical modelling of the flow in an isolated axial flow compressor rotor. The rotor is analyzed at four operating points, up to near stall conditions. Numerical results are first validated versus available experimental data and then further exploited in order to illuminate flow patterns in the inter-blade region. The tip leakage impact on the main passage flow and losses level as well as the effect of blade loading on the hub corner stall extent and the radial displacement of the flow are fully detailed. In order to account for the rotor geometry, the modifications performed in an existing software are mainly concerned with the accurate modelling of the clearance which is formed above the curved blade tip; for this purpose, a local H-type mesh is embedded to the main passage grid.	en
heal.publisher	ASME, New York, NY, United States	en
heal.journalName	American Society of Mechanical Engineers (Paper)	en