GB715145A - Improvements in or relating to stator constructions for compressors - Google Patents

Abstract

715,145. Axial-flow compressors. UNITED AIRCRAFT CORPORATION. Dec. 28, 1951 [Feb. 27, 1951], No. 30296/51. Class 110(3) [Also in Group XXII] In a stator construction for an axial-flow compressor, comprising a series of radially-extending stator vanes supported by a shroud, the shroud is in the form of spaced apart, concentrically arranged ring elements connected together to prevent relative motion between them. The outer ends of stator blades 10, Fig. 3, are inserted into a support ring 40 by a punching operation in which each blade acts as a punch, backed up by a die 66. A clamp 64 engages each blade and drives it through the ring 40. A spacer 44, Fig. 6, is then attached, as by welding, to the ring 40. and a further ring 42 is attached to the spacer. The blade 10 is then punched through the ring 42, spacing members 68 being used during this operation. A further spacer 46, Fig. 2, is then attached. To improve the punching action, the trailing edge of the blade may be cut back at 67. The inner end of each blade 10 is inserted into a notch 74, Fig. 7, shaped approximately to the blade contour and formed in a flange 76 of a ring 75. The blade is notched at 82 to engage a flange 72 of a ring 70. The rings 70 and 75 are then secured together, as by welding. Angled surfaces 86 and 87, on the flange 72 and blades 10 respectively, co-operate to provide a wedging action on assembly. The shroud ring formed by the parts 40, 42, 44, 46 may be made up of two or more segments. In any case, the ring is split into halves prior to assembly of the compressor, to permit the rows of stator blading to be intercalated with the rows of blading of the previously-assembled rotor. Spacer rings 34 are inserted between each row of stator blading and have lugs 36 which locate the stator assembly relative to the casing 4.