An apparatus 30 for improving heat transfer through a leading portion of an aircraft engine 11. The apparatus 30 includes an annular channel that is defined by the leading portion. A source for gas is fluidly connected to the channel and a narrow region 40 that is defined within the annular channel.
DIRECTIONAL FLOW NOZZLE SWIRL ENHANCER
DIREKTIONALER STRÖMUNGSDÜSENDRALLVERSTÄRKER
DISPOSITIF AMÉLIORANT L'EFFET TOURBILLONNAIRE D'UNE BUSE
2017-11-08
Patent
Elektronische Ressource
Englisch
Kraftfahrwesen | 1981
|Evolution of swirl in two-dimensional-nozzle flow
AIAA | 1982
|