JPH032641Y2 - - Google Patents

Description

[Detailed Description of the Invention] (Industrial Application Field) The present invention relates to a connecting plate damper that connects groups of rotor blades connected by a shroud.

(Prior Art) Conventionally, when fixing the rotor blade ends of a turbine, for example, three rotor blades are grouped together as shown in FIGS. 4 to 7,
The holes 4 of the connecting plate damper 3 are inserted into the tenons 2, 2 at the tips of the rotor blades 1, 1 located at the adjacent ends of each group, and the shroud 5 for the 3 rotor blades is inserted above the connecting plate damper 3.
The three holes of the shroud 5 for the third rotor blade were inserted into the tenon 2, and the tenon 2 was caulked to fix the shroud 5, the rotor blade 1, and the connecting plate damper 3 to each other.

(Problems to be Solved by the Invention) In the fixing method of the rotor blade end shown in FIGS. 4 to 7, after the connecting plate damper 3 is installed, one of the connecting plate dampers 3 is damaged and has to be removed. When replacing with a new connecting plate damper 3, there was a problem that the rotor blades 1 and shroud 5 were deformed during removal, making it necessary to replace all the rotor blades 1, which required considerable effort and cost.

(Means for Solving the Problems) The present invention addresses the above-mentioned problems, and includes a connecting plate damper that interconnects blade groups in which the tips of turbine rotor blades are connected by a shroud. A plate material having portions formed at predetermined intervals is inserted between the shroud and the end surface of the turbine rotor blade at the end of the blade group from at least the forward and reverse directions of the turbine axis, and the tip of the plate material is The multi-connection plate damper is characterized by being bent toward the shroud, and its purpose is to increase the vibration damping effect of turbine rotor blades. Another object of the present invention is to provide a multi-connection plate damper that does not require replacing all rotor blades when replacing the connection plate damper.

(Example) Next, the multiple connection plate damper of the present invention will be explained with reference to an example shown in FIGS. 1 to 3. Connection plate damper 3'
is made of a parallelogram steel plate, and two grooves 6, 6 parallel to the diagonal sides are provided so that the tenons 2', 2' can be inserted into adjacent tenons 2', 2'. A tenon 2' of a group of plural rotor blades and a shroud 5' are integrally fixed. A gap 7 is provided between the edge of the rotor blade 1 at both ends of the rotor blade group 1 and the shroud 5',
Connecting plate dampers 3',
3' is press-fitted while inserting its grooves 6, 6 into the tenons 2', 2'. After the press-fitting is completed, the ends of the connection plate dampers 3', 3' are bent toward the shroud 5' to form bent portions 8, 8. In this embodiment, a double connecting plate damper 3' is shown, but a multiple connecting plate damper 3' may be used.

(Function) Next, the function of the multiple connection plate damper will be explained.
Since the connecting plate damper 3' mutually connects and fixes the group of rotor blades connected and fixed by the shroud 5', the tips of the turbine rotor blades 1 are all connected and fixed by the plurality of connecting plate dampers, and the rotor blades The rigidity of the structure 1 is further strengthened compared to the conventional example, and dangerous resonance phenomena are less likely to occur. Furthermore, due to the plurality of connecting plate dampers 3', the number of friction surfaces between the shroud 5' and the connecting plate dampers 3' is larger than in the conventional example, and the vibration damping effect is increased. Also, if it becomes necessary to replace the connecting plate damper 3',
Since the bent part 8 of the connecting plate damper 3' is stretched and pulled out from the gap 7, at most only a few nearby rotor blades 1 and the shroud 5' will be damaged, and the rotor blades 1 around the entire circumference will be damaged. No need to replace. Furthermore, since the end of the connecting plate damper 3' is bent, there is no fear that it will come off due to centrifugal force.

(Effects of the invention) As described above, the present invention is a connecting plate damper that interconnects blade groups in which the tips of turbine rotor blades are connected by a shroud, in which notches are formed at a predetermined interval on one side. Since the plate material is inserted between the shroud and the end surface of the turbine rotor blade at the end of the blade group from at least the forward and reverse directions of the turbine axis direction, and the tip of the plate material is bent toward the shroud side,
The rigidity of the rotor blades has been strengthened, making it less likely that dangerous resonance phenomena will occur, and the friction damping effect has also been increased. Furthermore, when replacing the connecting plate damper, there is no need to replace all the moving blades, which has the effect of reducing the effort and cost of replacing the connecting plate damper.

[Brief explanation of the drawing]

FIG. 1 is a cross-sectional front view showing an embodiment of the multi-connection plate damper of the present invention, FIG. 2 is a plan view of FIG. 1, FIG. 3 is a plan view of the connection plate damper of the present invention, and FIG. A side view showing a conventional turbine rotor blade end fixing method,
5 is a cross-sectional front view of FIG. 4, FIG. 6 is a plan view of FIG. 4, and FIG. 7 is a plan view of a conventional connecting plate damper. 1... Moving blade, 3'... Connection plate damper, 6... Groove,
5'... Shroud, 8... Bend.

Claims (1)

[Scope of utility model registration request] In a connecting plate damper that interconnects blade groups in which the tips of turbine rotor blades are connected by a shroud, a plate with cutouts formed at a predetermined interval on one side is connected to the shroud and the turbine at the end of the blade group. 1. A multi-connection plate damper, characterized in that the plate material is inserted between the rotor blade end face from at least the forward and reverse directions of the turbine axis, and the tip of the plate material is bent toward the shroud side.