About: NUMERICAL INVESTIGATION of HIGHLY LOADED SINGLE-STAGE AXIAL-FLOW COMPRESSOR

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Description	Aerodynamic performance of highly loaded low-speed axial-flow compressor stage AV1 was computed by means of commercial code Fluent 6.3.26. The computed data were compared with experimental results obtained in test stage with external diameter of 600 mm. At design condition one could observe reasonable agreement. The difference between theoretical and measured characteristics increased with the growing distance of stage working point from design point. This conclusion is supported by the comparison of experimental and computed rotor and stator blade elements performance at three typical working conditions. Aerodynamic performance of highly loaded low-speed axial-flow compressor stage AV1 was computed by means of commercial code Fluent 6.3.26. The computed data were compared with experimental results obtained in test stage with external diameter of 600 mm. At design condition one could observe reasonable agreement. The difference between theoretical and measured characteristics increased with the growing distance of stage working point from design point. This conclusion is supported by the comparison of experimental and computed rotor and stator blade elements performance at three typical working conditions. (en) Aerodynamic performance of highly loaded low-speed axial-flow compressor stage AV1 was computed by means of commercial code Fluent 6.3.26. The computed data were compared with experimental results obtained in test stage with external diameter of 600 mm. At design condition one could observe reasonable agreement. The difference between theoretical and measured characteristics increased with the growing distance of stage working point from design point. This conclusion is supported by the comparison of experimental and computed rotor and stator blade elements performance at three typical working conditions. (cs)
Title	NUMERICAL INVESTIGATION of HIGHLY LOADED SINGLE-STAGE AXIAL-FLOW COMPRESSOR NUMERICAL INVESTIGATION of HIGHLY LOADED SINGLE-STAGE AXIAL-FLOW COMPRESSOR (en) NUMERICAL INVESTIGATION of HIGHLY LOADED SINGLE-STAGE AXIAL-FLOW COMPRESSOR (cs)
skos:prefLabel	NUMERICAL INVESTIGATION of HIGHLY LOADED SINGLE-STAGE AXIAL-FLOW COMPRESSOR NUMERICAL INVESTIGATION of HIGHLY LOADED SINGLE-STAGE AXIAL-FLOW COMPRESSOR (en) NUMERICAL INVESTIGATION of HIGHLY LOADED SINGLE-STAGE AXIAL-FLOW COMPRESSOR (cs)
skos:notation	RIV/49777513:23640/09:00502852!RIV10-GA0-23640___
http://linked.open...avai/riv/aktivita	P
http://linked.open...avai/riv/aktivity	P(GA101/09/1959)
http://linked.open...vai/riv/dodaniDat	2010
http://linked.open...aciTvurceVysledku	Dvořák, Dalibor Polanský, Jiří
http://linked.open.../riv/druhVysledku	O - Ostatní výsledky nezařaditelné do žádného z výše uvedených druhů výsledku
http://linked.open...iv/duvernostUdaju	S - Úplné a pravdivé údaje nepodléhající ochraně podle zvláštních právních předpisů
http://linked.open...titaPredkladatele	Západočeská univerzita v Plzni / Nové technologie - výzkumné centrum
http://linked.open...dnocenehoVysledku	330211
http://linked.open...ai/riv/idVysledku	RIV/49777513:23640/09:00502852
http://linked.open...riv/jazykVysledku	cze - čeština
http://linked.open.../riv/klicovaSlova	axial-flow compressor; comparison; aerodynamic characteristics (en)
http://linked.open.../riv/klicoveSlovo	aerodynamic characteristics axial-flow compressor comparison
http://linked.open...ontrolniKodProRIV	[C995A7D8BAD4]
http://linked.open...in/vavai/riv/obor	BK
http://linked.open...ichTvurcuVysledku	2 (xsd:int)
http://linked.open...cetTvurcuVysledku	2 (xsd:int)
http://linked.open...vavai/riv/projekt	Passive and active flow control in channels of centrifugal stage with forward curved blades
http://linked.open...UplatneniVysledku	2009
http://linked.open...iv/tvurceVysledku	Polanský, Jiří Dvořák, Dalibor
http://localhost/t...ganizacniJednotka	23640

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