GB1137940A - Improvements in frame structure for a gas turbine engine - Google Patents

Abstract

1,137,940. Gas turbine jet engines. GENERAL ELECTRIC CO. Dec. 14, 1966 [April 7, 1966], No. 55933/66. Headings F1J and F1T. A frame structure for a gas turbine engine having substantially concentric co-axial outer and inner casings forming an annular fluid-flow passage therebetween for the flow of hot exhaust gases, comprises ring members formed with radially outwardly directed fins which are secured in abutment to the outer casing and to an intermediate or spacing member, a plurality of peripherally spaced struts being secured to the inner casing and to the outer casing axially between the rings. The temperatures of the exhaust gases are communicated directly to the rings to reduce thermal stresses. The frame structure shown extends between the outer and inner casings 24, 22 at the discharge side of the turbine 16, the frame structure comprising radial struts 26 and serving to support the shaft bearing 18. The outer ring comprises a pair of T-shaped ring members disposed with their stems 32, 34 directed radially outwardly, the bases 36, 38 being spaced apart by a ring member 40 to which they are secured, the bases 36, 38 being also secured to the outer casing 24. The outer ring member is formed of four segmental parts as shown in Fig. 2 and four segmental parts as shown in Fig. 3 the parts being secured together to form a complete ring as shown in Fig. 5. The segmental parts as shown in Fig. 3 comprises a stub 46 to which the struts 26 are secured, the whole of the segmental parts as shown in Fig. 3 including the stub strut portion being formed by casting. The parts corresponding to the T-section ring members shown in Fig. 2 are indicated by the same reference numerals 28, 30, 32, 34, 36, 38. Openings 48 are provided in the stem portions 32, 34 to facilitate welding.