JPH01134701U - - Google Patents

Description

[Brief explanation of the drawing]

Fig. 1 is a cross-sectional view of a rotor blade row according to an embodiment of the present invention taken along a plane perpendicular to the turbine rotation axis, Fig. 2 is an enlarged view of the part shown in Fig. 1, and Fig. 3 is a cross-sectional view of the part shown in Fig. 2.
4 is a plan view of the damper piece used in the same embodiment, FIG. 5 is a side view, FIG. 6 is a cross-sectional view of FIG. 4, and FIG. 7 is a conventional T-shaped route.・Diagram showing the integral shroud wing, No. 8
The figure also shows a cross-sectional view of a conventional rotor blade row taken along a cylindrical surface coaxial with the turbine rotating shaft (the dashed line in Figure 9), and Figure 9 is a cross-sectional view taken along the chain line in Figure 8.
Figures 10 and 11 are respectively similar to Figure 9.
Cross-sectional view according to dashed lines and dashed lines, 1st
FIG. 2 is a plan view showing a groove for installing a wing, and FIG. 13 is a perspective view thereof. 1, 1a, 1b, 1c, 1d, 1e...T-shaped root integral wing, 1a...final implanted wing, 2...
Wing part, 3... Root part, 4, 4d, 4e... Shelf part, 5
... impeller, 6 ... groove of inverted T-shaped cross section, 7 ... vertical groove, 8 ... stop key, 9 ... connection piece, 10 ... damper piece.

Claims (1)

[Scope of utility model registration request] In an integral wing assembly with a T-shaped root and a serration wing stop device, a gap is provided between the blade ledges adjacent to the stop key that narrows outward in the turbine radial direction, and the gap is fitted into the gap. An integral wing assembly characterized in that mating damper pieces are inserted and caulked.