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Statements

Subject Item
n2:RIV%2F61388998%3A_____%2F10%3A00346318%21RIV11-GA0-61388998
rdf:type
n9:Vysledek skos:Concept
dcterms:description
This paper deals with an analysis of the flow through a high cambered compressor blade cascade. The profiles of the blade cascade have been designed to be of MCA-type. The geometric and aerodynamic parameters of the cascade are presented here. The aerodynamic research was performed in a transonic wind tunnel. Optical methods were applied to obtain information on the flow structures aking place in the interblade channels when operating in a range of subsonic and transonic velocities and at various angles of incidence. The internal shock waves and the flow separation in the rear part of the cascade channel were bserved and studied. Their influence on the loss coefficient and exit flow angle at subsonic and low transonic region was assessed. The thickness of the sidewall boundary layer in the interblade channel was measured in order to investigate the development of the axial velocity density ratio (AVDR), which plays an important role in the interpretation of the results. This paper deals with an analysis of the flow through a high cambered compressor blade cascade. The profiles of the blade cascade have been designed to be of MCA-type. The geometric and aerodynamic parameters of the cascade are presented here. The aerodynamic research was performed in a transonic wind tunnel. Optical methods were applied to obtain information on the flow structures aking place in the interblade channels when operating in a range of subsonic and transonic velocities and at various angles of incidence. The internal shock waves and the flow separation in the rear part of the cascade channel were bserved and studied. Their influence on the loss coefficient and exit flow angle at subsonic and low transonic region was assessed. The thickness of the sidewall boundary layer in the interblade channel was measured in order to investigate the development of the axial velocity density ratio (AVDR), which plays an important role in the interpretation of the results.
dcterms:title
AERODYNAMIC RESEARCH ON THE MCA – TYPE COMPRESSOR BLADE CASCADE AERODYNAMIC RESEARCH ON THE MCA – TYPE COMPRESSOR BLADE CASCADE
skos:prefLabel
AERODYNAMIC RESEARCH ON THE MCA – TYPE COMPRESSOR BLADE CASCADE AERODYNAMIC RESEARCH ON THE MCA – TYPE COMPRESSOR BLADE CASCADE
skos:notation
RIV/61388998:_____/10:00346318!RIV11-GA0-61388998
n4:aktivita
n8:Z n8:P
n4:aktivity
P(GA101/08/0623), P(GAP101/10/1329), P(IAA200760801), Z(AV0Z20760514)
n4:dodaniDat
n11:2011
n4:domaciTvurceVysledku
n16:5890780 n16:2157810
n4:druhVysledku
n18:D
n4:duvernostUdaju
n7:S
n4:entitaPredkladatele
n21:predkladatel
n4:idSjednocenehoVysledku
245571
n4:idVysledku
RIV/61388998:_____/10:00346318
n4:jazykVysledku
n17:eng
n4:klicovaSlova
compressor blade cascade; transonic flow; aerodynamic research
n4:klicoveSlovo
n5:compressor%20blade%20cascade n5:aerodynamic%20research n5:transonic%20flow
n4:kontrolniKodProRIV
[F5E25499B29D]
n4:mistoKonaniAkce
Glasgow
n4:mistoVydani
Glasgow
n4:nazevZdroje
Proceedings of ASME Turbo Expo 2010: Power for Land, Sea and Air GT2010
n4:obor
n20:BK
n4:pocetDomacichTvurcuVysledku
2
n4:pocetTvurcuVysledku
3
n4:projekt
n6:IAA200760801 n6:GAP101%2F10%2F1329 n6:GA101%2F08%2F0623
n4:rokUplatneniVysledku
n11:2010
n4:tvurceVysledku
Šimurda, David Šafařík, P. Luxa, Martin
n4:typAkce
n12:WRD
n4:zahajeniAkce
2010-06-14+02:00
n4:zamer
n15:AV0Z20760514
s:numberOfPages
10
n14:hasPublisher
ASME
n13:isbn
978-0-7918-3872-3