EP 0823539 B1 20020410 - Influencing the boundary layer on turbomachinery blades
Title (en)
Influencing the boundary layer on turbomachinery blades
Title (de)
Grenzschichtbeeinflussung bei Turbomaschinenschaufeln
Title (fr)
Méthode pour influencer la couche limite sur des aubes de turbomachines
Publication
Application
Priority
DE 19632207 A 19960809
Abstract (en)
[origin: EP0823539A2] The turbo-machine comprises at least one rotor disc supporting several blades and with intermittent flow fluid pulses blowing in the vicinity if the boundary layer detachment area via channels which issue into apertures on blade surface. On the face side of the rotor disc, a stationary ring with at least one through passage aperture is provided, with which the entry apertures in the rotor disc for the blade fluid channels periodically come to cover. In this way, the flow fluid is able to reach the fluid channels from a chamber located in front of the rotor disc in intermittent form as fluid pulses via the at least one through passage aperture. The size and-or the number of through passage apertures in the stationary ring is matched to the required blow-in frequency of the intermittent fluid pulse.
IPC 1-7
IPC 8 full level
F01D 5/14 (2006.01); F03B 13/04 (2006.01)
CPC (source: EP US)
F01D 5/145 (2013.01 - EP US); F05D 2260/16 (2013.01 - EP US); Y10S 415/904 (2013.01 - EP US)
Designated contracting state (EPC)
DE FR GB
DOCDB simple family (publication)
EP 0823539 A2 19980211; EP 0823539 A3 19991110; EP 0823539 B1 20020410; DE 19632207 A1 19980212; DE 59706939 D1 20020516; US 5876182 A 19990302
DOCDB simple family (application)
EP 97112247 A 19970717; DE 19632207 A 19960809; DE 59706939 T 19970717; US 90747897 A 19970811