JP3042095B2 - Gas turbine fastening device - Google Patents

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a fastening device for a gas turbine.

[0002]

2. Description of the Related Art FIG. 2 is a sectional view schematically showing an example of a conventional fastening device for a gas turbine. 1 is a two-stage compressor, and 2 is a two-stage turbine connected behind the compressor.

Reference numerals 3 and 4 denote impellers of a compressor.
Diffusers 7 and 8 having guide vanes 5 and 6 are formed between the impeller 3 and the impeller 4 and downstream of the impeller 4 so as to form a predetermined curve in a radial direction surrounding the outer periphery of each impeller 3 and 4. A combustor 9 is provided behind the diffuser 8, and a combustion chamber 10 is provided in the combustor 9.

[0004] Reference numerals 11 and 12 denote rotor blades of the turbine 2, which are coaxially arranged with the impellers 3 and 4 in the axial extending direction.
The outer peripheral blades of the rotor blades 11 and 12 are surrounded by an annular combustion gas duct 13 extending from the combustion chamber 10 of the combustor 9.

The impellers 3 and 4 of the compressor 1 and the moving blades 11 and 12 of the turbine 2 are connected to the impellers 3 and 4 respectively.
And a common tension bar 14 penetrating through the axis of each of the moving blades 11 and 12, between adjacent impellers 3 and 4, between each moving blade 11 and 12, and between the impeller 4 and the moving blade 11. The nut 15 is screwed into a threaded portion 14a which is screwed to the tip of the tension bar 14 on the moving blade 12 side, and the nut 15 is fixed to a predetermined torque. The impellers 3, 4 and the rotor blades 11, 12 are integrally fastened by tightening.

Thus, each impeller 3 of the compressor 1
4 is rotationally driven by an external driving device (not shown) through a tension bar 14 so that air is sucked into the compressor 1, the flow speed of the air is increased by the impellers 3 and 4, and the diffuser 7 of the compressor 1 is , 8 and the guide vanes 5, 6 provided in the diffusers 7, 8 convert the flow velocity of the air into pressure.
Compress the air.

Further, the compressed air is introduced into a combustion chamber 10 of a combustor 9, mixed with fuel, and ignited to generate high-temperature and high-pressure combustion gas. The combustion gas is supplied to a turbine 2 by a combustion gas duct 13. The rotating blades 11 and 12 of the turbine 2 are driven to generate power.

[0008]

However, in the above-described gas turbine fastening device, the impellers 3 and 4 of the compressor 1 and the moving blades 11 and 12 of the turbine 2 are radially elongated by centrifugal force generated during high-speed rotation. The tension bar 14 which fastens the impellers 3 and 4 and the moving blades 11 and 12 in the axial direction must be pre-tensioned in consideration of elongation corresponding to the shrinkage allowance. There is.

For this purpose, a large tightening force is required, and the entire length of the tension bar 14 having a diameter corresponding to the tightening force must be formed of expensive special alloy steel, which is uneconomical. There were problems such as difficulty.

The present invention has been made in view of the above circumstances, and has as its object to provide a gas turbine fastening device that can solve the above problem by dividing a tension bar into two.

[0011]

SUMMARY OF THE INVENTION The present invention provides a multi-stage coaxial
Contact the fastening device for a gas turbine which is adapted for fastening to <br/> integrally clamped axially between the impeller and the rotor blades of the turbine side <br/> of juxtaposed compressor side by the tension bar < and the tension bar between the compressor side and the turbine side.
Is divided in the axial direction at the boundary position of
One of the tension bars allows the compressor side impeller
And can be fastened independently.
The tension bar is connected to the turbine of the one tension bar.
Connected to the side end and each blade on the turbine side independently
It is characterized in that it is configured to be able to be fastened .

[0012]

Therefore, according to the present invention, after inserting a tension bar for fastening the compressor impeller through a plurality of compressor impellers and tightening them by a predetermined fastening force, a turbine rotor blade is fastened to the turbine side end of the tension bar. A tension bar is connected, the tension bar is inserted into the turbine blade, and tightened by a predetermined fastening force, thereby integrally fastening the compressor impeller and the turbine blade.

[0013]

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

FIG. 1 is a sectional view schematically showing a gas turbine fastening device according to the present invention. The basic structure other than a tension bar is substantially the same as the conventional gas turbine fastening device shown in FIG. is there. In the figure, the same components as those shown in FIG.
Hereinafter, a configuration specific to the present invention will be described.

In the gas turbine fastening device of this embodiment,
A tension bar 16 having a diameter and a length capable of penetrating the shaft cores of the impellers 3 and 4 of the compressor 1, having a large diameter portion 16 a at a base portion, and a screw portion 16 b screwed at a distal end portion is provided. .

Further, a female thread 17a having a diameter and a length capable of penetrating the axis of each of the moving blades 11 and 12 of the turbine 2 and capable of being screwed to the tip thread 16b of the tension bar 16 is provided at the base. And a tension bar 17 having a threaded portion 17b screwed at the tip.

The tension bar 16 penetrates through the axis of each of the impellers 3 and 4 from the front of the impeller 3 with the tip end first, and is extended by applying a predetermined tension (for example, 5 Ton) to the tension bar 16. After the nut 18 screwed to the screw portion 16b is tightened with a predetermined torque so that the nut 18 is always in close contact with the compressor impeller 4, the impellers 3 and 4 are removed by removing the tension.
Are fastened together.

A threaded portion 17a is provided at the distal end of the tension bar 16 at the base of the tension bar 17.
By connecting the tension bar 16 and the tension bar 17 by external fitting, the tension bar 17 penetrates through the axis of each of the moving blades 11 and 12 from the front of the moving blade 11 with the tip end first. A predetermined tension (for example, 3 Ton or 4 Ton) is applied to the tension bar 17 and stretched, and the nut 19 screwed to the screw portion 17 b is tightened with a predetermined torque.
The impellers 3 and 4 are integrally fastened together with the impellers 3 and 4 by the tension bar 16, and the rotor blades 11 and 12 are integrally fastened together.

The operation of generating power by the gas turbine is the same as the operation of the conventional example shown in FIG.
The following description is omitted.

According to the above, the tension bars 16, 17
Is divided into two parts, and the impellers 3, 4 and the moving blades 11, 12 are formed so as to be fastened by separate tension bars 16 and tension bars 17, so that the impellers 3, 4 and the moving blades 11, 12 are formed. The diameter, length, and material required for each can be individually and appropriately selected, which is extremely economical.
Since the length 12 is shortened, processing and handling can be easily performed.

The present invention is not limited to the above-described embodiment. For example, a female screw is screwed into the tip of the tension bar 16 and the female screw is screwed into the base of the tension bar 17. The tension bar 16 and the tension bar 17 may be connected by providing a screw portion to obtain the screw portion and screwing the screw portion to the female screw. It is needless to say that various changes can be made without being limited and without departing from the gist of the present invention.

[0022]

According to the fastening device for a gas turbine of the present invention, each impeller and each moving blade are formed so as to be able to be fastened by a separate tension bar, so that the diameter required for each impeller and each moving blade is required. , Length and material can be selected individually and appropriately, which is extremely economical. In addition, since each tension bar is short, it is easy to process and handle. The effect can be obtained.

[Brief description of the drawings]

FIG. 1 is a sectional view schematically showing a fastening device for a gas turbine according to the present invention.

FIG. 2 is a cross-sectional view schematically illustrating an example of a conventional gas turbine fastening device.

[Explanation of symbols]

 DESCRIPTION OF SYMBOLS 1 Compressor 2 Turbine 3 Impeller 4 Impeller 11 Moving blade 12 Moving blade 16 Tension bar 17 Tension bar

Continuation of the front page (56) References JP-A-60-11634 (JP, A) JP-A-52-96106 (JP, U) (58) Fields investigated (Int. Cl. ⁷ , DB name) F02C 7 / 20 F01D 25/00 F02C 7/00

Claims (1)

(57) [Claims] 1. A compressor which is coaxially arranged in multiple stages.
In the fastening device of <br/> gas turbine so as to fasten together by tightening the respective rotor blades of the impeller and the turbine side of the side in the axial direction by the tension bar, co the tension bar
Two minutes in the axial direction at the boundary position between the compressor side and the turbine side
Split and use one of the two tension bars
Each impeller on the compressor side can be fastened independently.
And the other tension bar is
To the turbine end of the tension bar
A fastening device for a gas turbine, characterized in that the blades on the turbine side can be fastened independently .