JP2000230405A - Seal for gas turbine stator blade tip - Google Patents

Abstract

PROBLEM TO BE SOLVED: To provide a tip seal for a turbine stator blade having a structure to permit mounting in a correct right-to-left condition. SOLUTION: This turbine stator blade tip seal, a tip of a turbine stator blade is provided with rings 12, 13 and the rings are sealed by a ring-shaped seal 1 mounted on a rotor 2. The annular seal 1 is closely attached and fastened by a bolt 9 to a supporting face of a seal support member 7 perpendicular to a turbine axis 6. A projection 1e is constructed on a surface opposite the supporting face proximate a bolt hole in the ring-shaped seal 1.

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a turbine vane tip seal in which a ring provided at the tip of a turbine vane row is sealed with a seal provided on a rotor.

[0002]

2. Description of the Related Art FIG. 3 shows a conventional seal structure for sealing a ring provided at the tip of a turbine vane of a jet engine. A rotor blade 5 is attached to a rotor 2 that rotates around a turbine shaft 6, and a stator blade 4 is attached to a stator 3 provided around the rotor 2. The rotor 2 is provided with a seal supporting member 7 having a circumferential surface orthogonal to the turbine shaft 6, and the stator blade seal 1 having a cross section as shown in FIG. A blade supporting member 8 having a circumferential surface which is also perpendicular to the turbine shaft 6 with the stationary blade seal 1 and the supporting member 7 interposed therebetween is provided, and a bolt 9 penetrates the four members 1, 7, 8, 8. The bolt 9 is fastened with a nut 10. This bolt 9
Is hung on the bolt head 9a and the bucket support member 8. A stationary blade tip ring 12 is provided at the tip of the stationary blade 4, and a sliding ring 13 is further provided on the inner surface of the stationary blade tip ring 12, and is in contact with the distal end of the stationary blade seal 1.

FIG. 4 shows a cross section taken along line XX of FIG. Bolt holes 1a are provided on the inner peripheral side of the stator blade seal 1 at a constant pitch on the circumference, and the space between the bolt holes 1a is cut away to reduce the weight. I have. As shown in FIG. 1, the front end of the stationary blade seal 1 is formed of a double ring of a front seal portion 1c and a rear seal portion 1d.

[0004]

On the rear surface of the stator blade seal 1, a mark "AFT" indicating the rear surface is marked, and an operator at the time of assembling the turbine sees the mark and attaches the stator blade seal 1. It is attached to the seal support member 7 and is sandwiched by the blade support members 8. However, when the mark is overlooked, the stator vane seal 1 has a structure that can be attached even if it is turned upside down.
There was a risk that the turbine would be assembled upside down.
When mounted in reverse, there is a problem that the predetermined sealing performance is not exhibited.

The present invention has been made to solve such a problem. That is, an object of the present invention is to provide a turbine vane tip seal having a structure in which the seal cannot be attached even if the front-rear direction is mistakenly attached.

[0006]

In order to achieve the above object, according to the first aspect of the present invention, a turbine is provided in which a ring is provided at the tip of a turbine vane and the ring is sealed by a ring-shaped seal attached to a rotor. In the vane tip seal, the ring-shaped seal is closely attached to a support surface orthogonal to the turbine axis of a seal support member and is attached with a bolt, and is opposite to the support surface near a bolt hole of the ring-shaped seal. Are provided with projections.

Since a projection is provided on the surface of the ring-shaped seal opposite to the surface in contact with the support surface of the seal support, the surface of the ring-shaped seal having the projection is erroneously attached to the support surface of the seal support. In this case, since the projections are provided, they cannot be brought into close contact with the support surface, and the operator can immediately recognize that the mounting has been performed by mistake. Thus, even if the mark indicating the mounting direction is overlooked, the ring-shaped seal can always be mounted correctly.

According to the second aspect of the present invention, a bolt detent is provided for connecting the bolt head of the bolt and the projection.

As described above, the projection can be used as a member for stopping the rotation of the bolt, and when the ring-shaped seal is mounted on the opposite side, the projection for stopping the rotation does not appear. It turns out that it was attached to the contrary.

[0010]

DESCRIPTION OF THE PREFERRED EMBODIMENTS Preferred embodiments of the present invention will be described below with reference to the drawings. FIG. 1 shows a configuration of a turbine stator blade tip seal according to an embodiment of the present invention. FIG. 2 shows FIG.
2 is a sectional view taken along line XX of FIG.

In FIG. 1, a rotor 2 rotating about a turbine shaft 6 is provided with a moving blade 5, and a stator 3 surrounding the rotor 2 is provided with a stationary blade 4. The rotor 2 is provided with a seal supporting member 7 having a circumferential surface orthogonal to the turbine shaft 6, and the hollow disk-shaped stator vane seal 1 having a cross section as shown in FIG. Mounted. The stator blade seal 1 is made of a heat-resistant metal, for example, a nickel alloy or the like. The end surface of the moving blade supporting member 8 for supporting each moving blade 5 is also provided on the turbine shaft 6.
Are provided so as to sandwich the stator vane seal 1 and the seal support member 7 from both sides with this circumferential surface,
A bolt 9 penetrates the four members 1, 7, 8, 8 and the bolt 9 is fastened with a nut 10.

A stationary blade tip ring 12 is provided at the tip of the stationary blade 4, and a sliding ring 13 is provided on the inner surface of the stationary blade tip ring 12, and is in contact with the distal end of the stationary blade seal 1.
The sliding ring 13 is formed in a honeycomb shape.

FIG. 2 shows a cross section taken along line XX of FIG. The stator blade seal 1 is made of a hollow disk, and the seal portion is a front seal portion 1c
And a double ring of the rear seal portion 1d. Bolt holes 1a are provided on the inner circumference at a constant pitch on the circumference, and the space between the bolt holes 1a is cut away to reduce the weight, and a portion having the bolt hole 1a protrudes like a tooth 1b. Further, a projection 1e of the present invention is provided along the circumference on the inner peripheral side of the tooth 1b.

In FIG. 1, a bolt rotation stopper 11 is provided to prevent the bolt 9 from being loosened. The bolt rotation stopper 11 is adapted to hang on the bolt head 9 a and the projection 1 e of the stator blade seal 1.

With this configuration, when the stationary blade seal 1 is incorporated into the turbine, even if the surface having the protrusion 1e is erroneously mounted on the circumferential surface of the seal support member 7 by mistake, the seal cannot be brought into close contact with the protrusion 1e. Therefore, the operator can recognize the error. Further, even if the bolt 9 is tightened in an incorrect state, the bolt detent 11 does not engage the projection 1e, so that the assembly cannot be performed in an incorrect state.

[0016]

As described above, according to the present invention, the projection is provided on the stationary blade seal so that it cannot be assembled even if the stationary blade seal is erroneously attached. Therefore, the stationary blade seal can always be correctly assembled.

[Brief description of the drawings]

FIG. 1 shows the configuration of a turbine vane tip seal according to an embodiment.

FIG. 2 is a sectional view taken along line XX of FIG.

FIG. 3 shows a configuration of a conventional turbine vane tip seal.

FIG. 4 is a sectional view taken along line XX of FIG. 3;

[Explanation of symbols]

 Reference Signs List 1 stator blade seal 1a bolt hole 1b tooth 1c front seal portion 1d rear seal portion 1e projection 2 rotor 3 stator 4 stator blade 5 rotor blade 6 turbine shaft 7 seal support member 8 rotor support member 9 bolt 9a bolt head 10 nut 11 Bolt rotation prevention 12 Stator blade tip ring 13 Sliding ring

 ──────────────────────────────────────────────────続 き Continuing on the front page (72) Inventor Shigeo Morii 3-5-1 Mukodaicho, Tanashi-shi, Tokyo Ishikawashima-Harima Heavy Industries Co., Ltd. Inside the Tanashi Plant (72) Inventor Kazunori Kanatsu 3-chome, Mukodaicho, Tanashi-shi, Tokyo No.5-1 Ishikawashima Harima Heavy Industries Co., Ltd. Tanashi Factory F-term (reference) 3G002 HA02 HA11

Claims (2)

[Claims] 1. A turbine vane tip seal in which a ring is provided at a tip of a turbine vane and the ring is sealed by a ring-shaped seal attached to a rotor, wherein the ring-shaped seal is a turbine of a seal support member. A turbine stator blade tip, wherein the tip is attached to a support surface orthogonal to the axis by a bolt in close contact with a bolt, and a projection is provided on a surface opposite to the support surface near a bolt hole of the ring-shaped seal. Part seal. 2. The turbine vane tip seal according to claim 1, further comprising a bolt detent connecting the bolt head of the bolt and the projection.