GB905262A - Improvements in or relating to structures having annular gas flow passages therein - Google Patents

Abstract

905,262. Axial-flow compressors; gas turbine plant. ROLLS-ROYCE Ltd. Oct. 19, 1959 [Nov. 21, 1958], No. 37633/58. Classes 110 (1) and 110 (3). In a structure comprising an annular gasflow passage bounded by inner and outer walls between which extends a ring of struts, each strut comprises a radially-inner portion secured to the inner wall and a radially-outer portion secured to the outer wall, the two portions meeting in surfaces extending substantially parallel to the passage axis and being bolted together with the surfaces in abutment. A gas-turbine engine comprises a compressor 10 supplying air to combustion equipment 12 by way of a diffuser 13. Struts extending between the inner and outer walls 14, 15 of the diffuser each comprise flanged castings 16, 17 let into correspondingly-shaped holes in the inner and outer walls 14, 15 and welded thereto at 16b, 17b respectively. A hollow intermediate casting 18 is welded to the casting 17 (or may be formed integral with it). Sheet metal fairings 19, 20 are afterwards welded to the respective walls 14, 15 with lugs 19b, 20b overlapping respective lugs 16e, 18# on the castings 16, 18 and welded thereto. The walls 14, 15 are then brought into position with the castings 16, 18 abutting at a surface parallel to the engine axis and are secured together by bolts 21. There is a gap 29 between the fairings 19, 20. Air for de-icing or cabin pressurization is bled from the diffuser 13 through holes 22 into the struts and thence through holes 23 into an annular manifold 24. At its downstream end, the manifold 24 is supported partly by radial flanges 25 on the castings 17 and partly by arcuate T-section strips 26 welded to the wall 15 between the flanges 25