Secondary flow calculation method for one stage axial transonic flow compressors, including shock-secondary flow interaction

Kaldellis, J; Douvikas, D; Falchetti, F; Papailiou, KD

dc.contributor.author	Kaldellis, J	en
dc.contributor.author	Douvikas, D	en
dc.contributor.author	Falchetti, F	en
dc.contributor.author	Papailiou, KD	en
dc.date.accessioned	2014-03-01T02:47:53Z
dc.date.available	2014-03-01T02:47:53Z
dc.date.issued	1989	en
dc.identifier.issn	04021215	en
dc.identifier.uri	https://dspace.lib.ntua.gr/xmlui/handle/123456789/33415
dc.relation.uri	http://www.scopus.com/inward/record.url?eid=2-s2.0-0024867248&partnerID=40&md5=083a993e8fb764ec40c1f22ae9cecd3b	en
dc.subject.other	Flow of Fluids--Mathematical Models	en
dc.subject.other	Shock Waves	en
dc.subject.other	Secondary Flow Calculation Method	en
dc.subject.other	Viscous Flow	en
dc.subject.other	Compressors	en
dc.title	Secondary flow calculation method for one stage axial transonic flow compressors, including shock-secondary flow interaction	en
heal.type	conferenceItem	en
heal.publicationDate	1989	en
heal.abstract	A secondary calculation method is presented, which makes use of the meridional vorticity transport equation. Circumferentially mean flow quantities are calculated using an inverse procedure. The method makes use of the mean kinetic energy integral equation and calculates simultaneously hub and tip secondary flow development. Emphasis is placed upon the use of a coherent two-zone model and particular care is taken in order to describe adequately the flow inside an unbounded (external), semi-bounded (annulus) and fully-bounded (bladed) space. Along with the velocity field, the losses, the defect forces and the corresponding additional work realized inside the viscous wall shear layer are calculated for stationary and rotating flow.	en
heal.publisher	Publ by American Soc of Mechanical Engineers (ASME), New York, NY, United States	en
heal.journalName	American Society of Mechanical Engineers (Paper)	en