GB707810A - Improvements in and relating to radial flow turbines and compressors - Google Patents

Abstract

707,810. Turbines and compressors. ESCHER WYSS AKT.-GES. March 27, 1952 [March 30, 1951]. No. 7905/52. Classes 110(1) and 110(2) [Alsoin Group XXII] In a radial flow turbine or compressor rotor comprising two axially-spaced discs with blades 3 extending therebetween, each blade is made in at least two parts bent out of sheet metal, one part being secured by welding, brazing or soldering to one disc and a second part being similarly secured to the second disc before assembly of the rotor, the blade parts being connected together by means of lap joints upon assembly of the rotor. The blade part 3<SP>1</SP> is secured to the hub disc 1 by welding at 4 and the blade part 3<SP>2</SP> is secured to the cover disc 2 by welding at 5, the two blade parts 3<SP>1</SP>, 3<SP>2</SP> being secured together by spot welding at 6 upon assembly of the rotor. The inlet edge of one of the blade parts 7 may be bent back upon itself as in Fig. 6 to form an aerofoil section shape. In the embodiment shown in Figs 11, 12, 13, the blade part secured to the hub disc 15 comprises two parts 17<SP>1</SP>, and the blade part secured to the cover disc 16 comprises two parts 17<SP>2</SP> with an intermediate plate 18 therebetween, the two discs and associated blade parts being secured together upon assembly by welding at 19. The spaces between the blade parts and discs may be utilized for drawing off the boundary layer or for internal cooling of the the blades. In other embodiments, the edges of two blade parts may abut and be secured by a thick plate overlapping the two blade parts; or the two blade parts may be axially separated and connected by a pair of overlapping plates; or the blade parts may be folded to form U-sections which abut and an intermediate plate of C-section inserted in the folds.