JP3306998B2 - Turbine rotor - Google Patents

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a turbine rotor.

[0002]

2. Description of the Related Art FIGS. 3 and 4 show an example of a turbine rotor of a conventional gas turbine engine for an aircraft.
To be more specific, on the outer peripheral portion of the turbine disk body 1 having a substantially disk shape, a large number of rotor blade bodies 2 are fixed at substantially equal intervals in the circumferential direction of the turbine disk body 1.

[0003] In order to fix the rotor blade body 2 to the turbine disk body 1, a large number of fir trees are provided around the outer periphery of the turbine disk body 1 at substantially equal intervals in the circumferential direction and pass in the front-rear direction of the turbine disk body 1. A coupling groove 3 is provided, and the bucket main body 2 is connected to a dovetail-shaped firtree coupling section 4 by being inserted into the firtree coupling groove 3 of the turbine disk main body 1. 4 is constituted by a plate-shaped platform portion 6 provided at an end of a shank portion 5 extending in the radial direction of the turbine disk main body 1 and a wing portion 7 provided radially outside of the platform portion 6. I have.

The far tree coupling portion 4 of the moving blade main body 2 is connected to the far tree coupling groove 3 of the turbine disk main body 1 by being inserted in the front-rear direction of the turbine disk main body 1. Are prevented from being displaced in the radial direction of the turbine disk main body 1, but are not restrained in the rotation axis direction of the turbine disk main body 1.

In order to prevent the moving blade body 2 from being displaced in the direction of the rotation axis of the turbine disk body 1, annular restraining members 8, 9 are provided on both front and rear sides of the moving blade body 2, and the adjacent moving blade bodies 2 are provided. A damper 11 is provided between the shank portions 5 of
The rotor blade body 2 is restrained in the rotation axis direction of the turbine disk body 1, that is, in the front-rear direction of the rotor blade body 2.

An annular restraining member 8 provided on the front side of the rotor blade main body 2 has a disk connecting portion 12 that can abut on the front side of the turbine disk main body 1, and this disk connecting portion 12 is provided on the front side of the turbine disk main body 1. It has a far tree contact portion 13 that comes into contact with the front end of the fir tree coupling portion 4 of the bucket main body 2 when brought into contact.

The restraining member 9 provided on the rear side of the bucket main body 2 includes:
A disk connecting portion 14 capable of abutting on the rear side of the turbine disk main body 1, and a far tree connecting portion of the rotor blade main body 2 when the disk connecting portion 14 is abutted on the rear side of the turbine disk main body 1. 4 has a fir tree contact portion 15 that contacts the rear end.

A bolt hole 16 is formed in each of the restraining members 8 and 9 and the turbine disk main body 1. Thus, the respective restraining members 8 and 9 are formed so as to be fastened to the turbine disk body 1.

The damper 11 has an outer peripheral surface 19 between the firtree coupling grooves 3 of the turbine disk body 1.
, So as to contact the circumferential side surface of the shank portion 5.

In this manner, with the firtree coupling portion 4 of the rotor blade body 2 coupled to the firtree coupling groove 3 of the turbine disk body 1, the restraining members 8, 9 are bolted to the turbine disk body 1. Then, the restraining members 8 and 9
Abutments 13 and 15 of the rotor blade body 2 abut against the front and rear end faces of the firtree joint 4 and the frictional force generated by the contact between the damper 11 and the lower surface of the platform 6 The displacement of the blade body 2 in the front-rear direction with respect to the turbine disk body 1 is restricted.

[0011]

However, in the conventional damper 11, the damper 11 can be inserted between a pair of adjacent shank portions 5 only when the cross-sectional shape of the shank portion 5 of the rotor blade body 2 is rectangular. However, in recent years, since it is necessary to reduce the stress of the shank 5 and to make the cooling passage smooth, the shank 5
Is designed so that the cross-sectional shape of the conventional damper 11 changes smoothly, and there is a problem that the conventional damper 11 cannot be applied.

The present invention has been made in view of the above circumstances, and provides a turbine rotor capable of preventing vibration of a rotor blade body by providing a damper capable of strongly contacting the rotor blade body by centrifugal force during operation of a gas turbine engine. It is done for the purpose of doing.

[0013]

SUMMARY OF THE INVENTION In order to achieve the above object, the present invention provides a plate-shaped platform at the tip of a shank connected to a firtree joint of a base and an anti-shank provided at the platform. A plurality of blade bodies provided with blade portions extending to the side, and a fir tree coupling portion of these blade bodies is inserted into a fir tree coupling groove formed at substantially equal intervals in the circumferential direction of the turbine disk body, and the turbine disk In a turbine rotor in which a rotor blade body is connected to a main body, and annular restraining members abutting on front and rear end faces of a fir tree joint of the rotor blade body are attached to front and rear ends of the turbine disk body, a shank portion of each rotor blade body is provided. On one side surface, a support pin having a tip directed outward in the radial direction of the turbine disk body is provided, and the turbine pin is provided between the blade bodies adjacent to each other by the support pin. In both the platform portion of the blade body adjacent movably supported in the radial direction of the disk body and the turbine disk body side is disposed a damper that can abut.

[0014]

When the turbine disk rotates, a damper disposed between adjacent blade bodies strongly contacts both platforms of the adjacent blade bodies from the turbine disk body side by the action of centrifugal force, A frictional force is generated between the damper and the platform of the rotor blade body.

[0015]

Embodiments of the present invention will be described below with reference to the drawings.

FIGS. 1 and 2 are schematic views of an embodiment of a turbine rotor according to the present invention. In the drawings, the same components as those in FIGS. 3 and 4 are denoted by the same reference numerals.

In this turbine rotor, the shank portion 5 of the rotor blade body 2 has a substantially central portion of one of the two circumferential sides of the turbine disk body 1, the tip of which protrudes in a direction perpendicular to the side surface and has a leading end. 1, a support pin 24 facing outward in the radial direction is provided, and the shank 5 of the blade body 2 and the platform 6 and the restraining member 9 on the rear side adjacent to each other are provided.
And the shank 5 of the rotor blade body 2 in the space 25 surrounded by
And a slit 26 which has a cross-sectional shape capable of contacting the lower surface of the platform portion 6 and extends in the front and rear restraining members 8 and 9, and is capable of engaging with the support pin 24 near a substantially central portion in the longitudinal direction. A damper 27 is provided.

In the turbine rotor shown in FIGS. 1 and 2,
When the gas turbine engine is operated, a centrifugal force acts on the damper 27 due to the rotation of the turbine disk main body 1, and the damper 27 strongly contacts the platform portions 6 of the moving blade main bodies 2 adjacent to each other from the turbine disk main body 1 side,
A friction force is generated between the damper 27 and the platform 6 of the bucket main body 2.

The frictional force generated between the damper 27 and the platform 6 of the moving blade body 2 causes the moving blade body 2
Is prevented. .

It should be noted that the present invention is not limited to the above-described embodiment, and it is needless to say that various changes can be made without departing from the spirit of the present invention.

[0021]

As described above, according to the turbine rotor of the present invention, when the turbine disk rotates, the dampers provided between the adjacent moving blade main bodies cause the adjacent moving blades to act due to the centrifugal force. An excellent effect that vibration of the rotor blade body can be effectively prevented because the turbine disk body strongly contacts both of the platform parts of the body from the turbine disk body side and a frictional force is generated between the damper and the rotor blade body. Can be played.

[Brief description of the drawings]

FIG. 1 is a sectional view schematically showing an embodiment of a turbine rotor of the present invention.

FIG. 2 is a view taken in the direction of arrows II-II in FIG.

FIG. 3 is a cross-sectional view schematically illustrating an example of a conventional turbine rotor.

FIG. 4 is a view taken in the direction of arrows IV-IV in FIG. 3;

[Explanation of symbols]

 DESCRIPTION OF SYMBOLS 1 Turbine disk main body 2 Rotor blade main body 3 Fir tree coupling groove 4 Fir tree coupling part 5 Shank part 6 Platform part 7 Blade part 8 Restriction member 9 Restriction member 24 Support pin 27 Damper

──────────────────────────────────────────────────続 き Continued on the front page (58) Field surveyed (Int.Cl. ⁷ , DB name) F01D 5/16 F01D 5/26 F01D 5/30

Claims (1)

(57) [Claims] 1. A plurality of blade bodies each having a plate-shaped platform portion provided at the tip of a shank portion connected to a firtree coupling portion of a base portion, and having a wing portion extending toward the anti-shank portion side at the platform portion. The turbine blade body is joined to the turbine blade body by inserting the fartree coupling portions of the rotor blade bodies into the fartree coupling grooves formed at substantially equal intervals in the circumferential direction of the turbine disk body. In the turbine rotor having annular restraining members abutting on the front and rear end surfaces of the fir tree joint portion of the rotor blade body, a tip portion is formed on one side surface of the shank portion of each rotor blade body in a radial direction of the turbine disk body. A supporting pin facing in the direction of the center of the turbine disk. A turbine rotor characterized in that dampers capable of abutting from both sides of a turbine disk body are provided on both platforms of a rotor blade body.