The present invention relates to a shrouded fan for gas turbine engines, in particular for a boundary ingestion engine, wherein the fan (200) includes a hub (210), a plurality of blade bodies (220) extending radially outward from the hub (210) to a first partial shroud (230) and a plurality of blade tips (240, 240') extending radially outward from the partial shroud (230). The partial shroud (230) is arranged such as to be at an intersection with a boundary layer of the aircraft's fuselage, thus, counteracting unsteady loading by varying the blade-pitch-ratio. The fan (200) may additionally comprise an outer shroud (250) as well as a second partial span shroud (432). The quantity of blade tips (240) is higher than the quantity of blade bodies (220), allowing greater granularity control over amount of fluid ingested at any given radial position.
FAN FOR GAS TURBINE ENGINES HAVING MID-SPAN SHROUD
FAN MIT ZWISCHENDECKBAND FÜR ZWEISTROMTURBOSTRAHLTRIEBWERKE
SOUFFLANTE DE MOTEURS À TURBINE À GAZ AVEC CARÉNAGE INTERMÉDIAIRE
2021-05-19
Patent
Elektronische Ressource
Englisch
IPC: | F04D Strömungsarbeitsmaschinen , NON-POSITIVE-DISPLACEMENT PUMPS / B23P Sonstige Metallbearbeitung , OTHER WORKING OF METAL / B64C AEROPLANES , Flugzeuge / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / F01D Strömungsmaschinen [Kraft- und Arbeitsmaschinen oder Kraftmaschinen], z.B. Dampfturbinen , NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES |
TURBINE SHROUD DURABILITY ANALYSIS
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