| 摘要 |
1,226,297. Gas turbine engines - air intakes. MESSERSCHMITT-BOLKOW-BLOHM G. m.b. H. June 10, 1969 [June 18, 1968], No.29446/69. Heading F1G. [Also in Division F2] The invention relates to an air intake duct of a jet engine having a compressor and particularly to a seal device therefor. The engine 10 shown in Fig. 1 is mounted in an outer housing and comprises a compressor casing 12 at the forward end of which is mounted by flange connection 11, 26 a flexible tubular duct 20 formed for example of siliconerubber. The duct 20 is formed integrally with an annular inflatable portion 22 shown in the inflated position in Fig. 3 and in the deflated position in Fig. 4. The portion 22 is formed with a peripherally ribbed surface 25 which in the inflated position co-operates with surface 61 of the engine housing 60 so as to form a seal. In the deflated position the surface 25 is spaced from the surface 61 to facilitate engine removal. A leaf spring 24 is disposed within the seal member 22 to assist flattening when deflated. The member 22 is inflated when in operation by air tapped from the engine compressor 12 through line 30, see Fig. 5, a check valve 41 also a pressure relief valve 42 being provided in the line. The relief valve 42 co-operates with a lever 31 which is pivotally connected at (32) to the engine and at its other end to the engine housing. When the lever 31 is disconnected from the housing for engine removal, the lever moves to the chain line position Fig. 6 (not shown) in which it acts to open the relief valve 42 whereby the seal member 22 is deflated. The valve 42 may also be opened to drain moisture from the system. In a second embodiment, Fig. 7 (not shown), the seal member 22 is inflated by air from a ground installation compressor. The ends of the duct 20 are reinforced by metal rings 27, 28. |
