Patent ID: 8262359
Filing Date: 2012-09-11
Classification: F01D,Y10T

Abstract:
1. A turbine diaphragm comprising: an annulus of static blades, each static blade comprising an inner platform, an aerofoil, and an outer platform; and an outer diaphragm ring surrounding the annulus of static blades and welded to the outer platforms; wherein the inner platforms together form an inner diaphragm ring, confronting edges of the inner platforms have an interference fit with each other, and the aerofoils are in a state of torsional stress between the inner and outer platforms; (a) a first axially aligned edge portion, (b) a first edge portion inclined to the axial direction, (c) a second axially aligned edge portion, (d) a second edge portion inclined to the axial direction, and (e) a third axially aligned edge portion, wherein the first, second, and third axially aligned edge portions are circumferentially offset from each other to form first, second, and third axially extending crank shaped arms, the first inclined edge portion connecting the first and second axially aligned edge portions and the second inclined edge portion connecting the second and third axially aligned edge portions, the first and second inclined edge portions thereby forming first and second inclined crank shaped arms.