TURBOJET ENGINE OIL TANK BREATHING DEVICE Russian patent published in 2006 - IPC F02C7/06 

FIELD: aircraft engineering; by-pass turbojet engines.

SUBSTANCE: invention relates to breathing device for use in by-pass turbojet engines installed in supersonic planes. Invention can be used in oil systems of engines operating in other industries. Proposed turbojet engine oil tank breathing device contains system of main drain lines secured between front and rear walls of oil tank and connecting members, such as cover plates, support and ring. Drain main line system is made in form of three hollow, cylinders coaxially installed with radial clearances one in the other, and cylinder (pipe) with intake hole. Axis of cylinder (pipe) does not coincides with axis of coaxially installed hollow cylinders. Oil tank is connected with centrifugal breather through breathing main line and through centrifugal breather with atmosphere. Part of connecting members is made in form of at least two groups of cover plates complying with relationships: 1,0 ≤ [S₂/(S₁+S_cp)] ≤ 1.5 and 0,04 ≤ (∑l_cp)/L_mc) ≤ 1,0 where S₂ is area of cross sections of cylinders connected by group of cover plates formed between outer surface of smaller cylinder of two interconnected cylinders and inner surface of larger cylinder of two interconnected cylinders; S₁ is are of cross section formed by inner surface of smaller cylinder of two cylinders interconnected by group of cover plates; S_cp is summary area of cross section of cover plates in one group; ∑l_cp is summary length of all cover plates in one group; L_mc is mean length of hollow cylinders connected by said group of cover plates. Areas of cross section formed between outer surface of smaller of two connected cylinders and inner surface of larger of two connected cylinders and separated by cover plates of one group differ from each other by 20%, maximum.

EFFECT: optimization of operation of venting device.