A compressed gas ejection assembly 10 for a rotating wing aircraft blade 2 comprises a compressed gas passage 114 adapted to allow a substantially constant mass flow through the compressed gas ejection assembly 10 across at least a portion of the width of the compressed gas ejection assembly 10.
OPTIMISED NOZZLE GEOMETRY
2022-09-29
Patent
Electronic Resource
English
IPC: | B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / B05B Sprühvorrichtungen , SPRAYING APPARATUS / B64C AEROPLANES , Flugzeuge / F15D FLUID DYNAMICS, i.e. METHODS OR MEANS FOR INFLUENCING THE FLOW OF GASES OR LIQUIDS , Strömungsdynamik, d.h. Verfahren oder Vorrichtungen zum Beeinflussen der Strömung von Gasen oder Flüssigkeiten |
Optimised Tooth Flank Geometry for High Performance Transmissions
SAE Technical Papers | 2007
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