| 摘要 |
1,222,902. Gas turbine jet engines - rotor frame. GENERAL ELECTRIC CO. June 26, 1968 [June 26, 1967], No.30505/68. Addition to 1, 137, 940. Headings F1J and F1T. The invention relates to a frame assembly for a gas turbine engine, the assembly comprising an inner annular member, a coaxial outer annular member and a plurality of strut members interconnecting the two annular members. The outer annular member is of cylindrical form and comprises two axially-spaced rings secured to an outer casing, each ring having a fin member directed radially outwardly, the fins being aligned with the leading and trailing edges of the struts. The frame assembly 26 described is mounted downstream of the turbine 19 and serves to support a bearing 27 in which the turbine shaft 30 is rotatably mounted. The frame assembly comprises an inner annular member 40 and an outer annular member 42 with four aerofoil shaped struts 35 extending therebetween. The outer annular member is formed in sections 50, 61, and 63 welded together at 65, each ring section 50 having a radially-extending rib 52. The member is formed on its inner surface with four lugs 68 to which the radially outer ends of the struts 35 are secured by welding at 69. Strengthening ribs 70 are formed on the outer surface of the member opposite the lugs 68. An inner casing portion 44 is secured to the inner annular member 40 being formed with openings 46 through which the strut members 35 extend. The struts 35 may be disposed tangentially to the inner annular member 40 instead of radially as shown. |
