GB550326A - Improvements in or relating to tanks for use in aircraft - Google Patents

Abstract

550,326. Tanks. NAPIER & SON, Ltd., D., and TRYON,.H. C. June 30, 1941, No. 8198. [Class 69 (i)] Relates to tanks for aircraft containing liquid such as lubricating oil supplied by a pump to the engine or to auxiliary hydraulically-operated means, and comprises an outer chamber having fixed therein a vertically-extending inner chamber with an inlet at its upper end and a baffle constraining the liquid to swirl in a helical path downwardly, vanes in the lower part of the inner chamber straightening the liquid flow to an outlet in the lower part of the inner chamber from which a passage leads to the main delivery pipe, said passage also communicating with the lower part of the outer chamber. Interference with the supply, due to sudden movements of the aircraft, is thereby. prevented. As shown, an inner cylindrical chamber B is fixed to the upper end of the outer tank A and has a tangential inlet G<SP>1</SP> and a reduced lower end B<SP>2</SP> connected by a gauze or like permeable passage C to the outlet D. In the chamber B is a hollow shaft E carrying a helical baffle F and having a closed lower end from which vanes H radiate; the shaft E has holes E<SP>2</SP> by which escaping air may pass through the shaft E to atmosphere or the engine sunip. Within, the outer chamber are horizontal overlapping baffles J, K. In another form, the vanes H are disposed in the reduced part B2 of the inner chamber which is brought lower to depend into a cup-like recess in the bottom of the outer chamber and from which leads the outlet D; the gauze &c. C is then arranged in the annular space between the bottom of the outer tank and the part B<SP>2</SP>.