GB1298868A - Improvements in or relating to turbomachines - Google Patents

Abstract

1298868 Turbines; axial flow compressors and pumps SOC NATIONALE D'ETUDE ET DE CONSTRUCTION DE MOTEURS D'AVIATION 30 Nov 1970 [1 Dec 1969] 56744/70 Headings F1C, FIT A blade supporting structure in a turbine, compressor or pump comprises at least one corrugated annular member coaxial with the axis of the machine and perforated by apertures in which the blade ends are fitted. In one arrangement, Fig.1, the stator blades 1 of an axial flow compressor are mounted at their outer ends in apertures in a casing 2 constituted by skins 2b, 2c between which is sandwiched a member 2a having circumferentially extending corrugations. The blades 1 are secured in the apertures by welding or other bonding. Rings 4, 4a are welded to the ends of casing 2 to enable the latter to be secured to an adjacent casing. The inner ends of blades 1 are secured to a casing 3 consisting of skins 3b, 3c and a corrugated member 3a. In a modification Fig.2 (not shown), the corrugations of members 2a, 3a extend axially of the machine, whilst in a further arrangement Fig.5 (not shown) the corrugations of members 2a, 3a extend respectively circumferentially and axially. In Fig.8 the casing 2 comprises three superposed corrugated members 102a, 112a, 122a separated by intermediate skins 2e, 2f, the corrugations of the respective members being staggered and of different pitch. In a further arrangement Fig.6 (not shown) casing 2 consists of two superposed members, one having axial corrugations and the other circumferential. The corrugations may have the complex profile shown in Fig.9. Other constructions for securing casing 2 to an axially adjacent casing or within a surrounding outer casing are described.