JP2004150700A - Gas turbine facility - Google Patents

Abstract

<P>PROBLEM TO BE SOLVED: To provide a gas turbine facility capable of preventing early wear of a seal member by easily repairing change of a gap between a combustion gas outlet of a transition piece and a combustion gas inlet of a turbine part. <P>SOLUTION: The gas turbine facility 1 is composed so that the gaps K and L are provided in an opposing part of the combustion gas outlet 13 of the transition piece 5B and the combustion gas inlet 14 of the turbine part 2, and the gaps K and L are sealed by the seal members 21 and 22. A displacement adjusting means 28 is provided for adjusting displacements of the gaps between the transition piece 5 and the turbine part 2. <P>COPYRIGHT: (C)2004,JPO

Description

[0001]
TECHNICAL FIELD OF THE INVENTION
The present invention relates to a gas turbine facility, and more particularly to a gas turbine facility including a combustion device having a transition piece.
[0002]
[Prior art]
For example, as shown in Patent Literature 1, gas turbine equipment generally includes a turbine unit, a gas combustion unit that generates combustion gas, and a transition piece that rectifies the generated combustion gas and introduces the generated combustion gas into the turbine unit. A plurality of combustion devices.
[0003]
Since the transition piece generates thermal elongation in the combustion gas flow direction due to the combustion gas, a gap is provided between the combustion gas outlet of the transition piece and the combustion gas inlet of the turbine section in order to absorb the thermal elongation. Is provided. This gap is closed by a seal member that is engaged across the combustion gas outlet and the combustion gas inlet.
[0004]
[Patent Document 1] JP-A-6-323544 (FIG. 1)
[Problems to be solved by the invention]
According to the above-mentioned conventional technology, the engagement of the seal member with the combustion gas outlet and the combustion gas inlet is inclined due to a change in the gap due to the dimensional change of the combustion gas outlet and the combustion gas inlet over time, and the engagement portion is worn out early. There was a problem to do.
[0005]
An object of the present invention is to provide a gas turbine facility that can easily repair a change in a gap between a combustion gas outlet of a transition piece and a combustion gas inlet of a turbine section and prevent early wear of a seal member.
[0006]
[Means for Solving the Problems]
In order to achieve the above object, the present invention adjusts the gap between the transition piece combustion gas outlet and the turbine section combustion gas inlet between the transition piece and the turbine section, or changes the position of the transition piece to the turbine section. Therefore, a means for adjusting the pressure was provided.
[0007]
According to the above configuration, when the engagement of the seal member straddling the combustion gas outlet and the combustion gas inlet is inclined, the gap between the opposed combustion gas outlet and the combustion gas inlet is adjusted by the adjusting means. Alternatively, by adjusting the position of the transition piece with respect to the turbine section, the facing gap between the combustion gas outlet of the transition piece and the combustion gas inlet of the turbine section can be returned to a normal state. As a result, the engagement of the seal member returns to the normal engagement, thereby preventing early wear of the seal member and maintaining the sealing effect for a long time.
[0008]
BEST MODE FOR CARRYING OUT THE INVENTION
Hereinafter, a first embodiment of a gas turbine facility according to the present invention will be described with reference to FIGS.
[0009]
The gas turbine equipment 1 is roughly divided into a turbine section 2, a compressor 3 located upstream of the turbine section 2 to generate compressed air, and a high-temperature, high-pressure high- And a combustion device 4 for generating combustion gas. The combustion device 4 has a gas combustion section 5A for burning fuel, and a transition piece 5B for rectifying and guiding the generated combustion gas to the turbine section.
[0010]
The turbine unit 2 includes a rotating shaft 6 that is supported by a shaft, moving blades 7 that are radially mounted around the rotating shaft 6 and that are arranged in multiple stages in the axial direction, and a casing that covers the outer periphery of the moving blade 7. And a multi-stage stationary blade 9 provided on the inner periphery of the casing 8 and protruding toward the center of the rotating shaft 6 and arranged between the multi-stage moving blades 7.
[0011]
Similarly to the turbine section 2, the compressor 3 has a configuration including a moving blade 11 attached to a rotating section 10 concentric with the rotating shaft 6 and a stationary blade 12 attached to a fixed section.
[0012]
The plurality of combustion parts 5A are installed concentrically around the rotation shaft 6.
[0013]
As shown in FIG. 2, the upstream side of the combustion gas of the transition piece 5B is connected to the combustion gas outlets of the plurality of combustion sections 5A, and the combustion gas outlet 13 of the transition piece 5B that is the downstream side of the combustion gas is It is connected to a combustion gas inlet 14 of the turbine section 2. The plurality of transition pieces 5B are also installed concentrically about the rotation shaft 6. As shown in FIG. 4, the combustion gas outlet 13 has a fan shape formed by an inner peripheral edge 16, an outer peripheral edge 17, and radial edges 18A and 18B connecting both edges. The space between the radial edges 18A and 18B of the adjacent combustion gas outlets 13 is closed and airtight.
[0014]
On the other hand, the combustion gas inlet 14 of the turbine section 2 is formed with an inner peripheral edge 19 and an outer peripheral edge 20 facing the inner peripheral edge 16 and the outer peripheral edge 17 of the combustion gas outlet 13.
[0015]
By the way, the transition piece 5B undergoes thermal expansion in the direction of flow of the combustion gas during operation. Therefore, in consideration of the thermal expansion, gaps L and K are formed in the facing portion between the combustion gas outlet 13 and the combustion gas inlet 14. Provided. In order to close the gaps L and K, the seal members 21 and 22 are engaged over the combustion gas outlet 13 and the combustion gas inlet 14.
[0016]
These sealing members 21 and 22 have U-shaped cross-sections 21a and 22a and an extending portion 21b extending perpendicularly outward from one of the U-shaped legs so as to follow changes in the gaps L and K. 22b.
[0017]
Engagement grooves for engaging the seal members 21 and 22 are formed in the inner peripheral edges 16 and 19 and the outer peripheral edges 17 and 20 of the combustion gas outlet 13 and the combustion gas inlet 14, respectively. To be more specific, the inner peripheral portion of the inner peripheral edge 16 of the combustion gas outlet 13 and the outer peripheral portion of the outer peripheral edge 17 are open toward the inner diameter side and the outer diameter side, and have an arc shape centered on the rotating shaft 6. Axial engagement grooves 23, 24 are formed. In the end faces of the inner peripheral edge 19 and the outer peripheral edge 20 of the combustion gas inlet 14, circumferential engagement grooves 25 and 26 that open toward the combustion gas outlet 13 are formed.
[0018]
One leg of the U-shaped cross section 21a, 22a of the seal member 21, 22 is inserted into and engaged with the axial engagement grooves 23, 24 formed as described above from the inner diameter side and the outer side. As a result, the engagement grooves 23 and 24 and the seal members 21 and 22 are in an engaged state in which displacement is possible in the radial direction but displacement is restricted in the axial direction. On the other hand, the extending portions 21b and 22b of the seal members 21 and 22 are inserted into and engaged with the circumferential engagement grooves 25 and 26 from the axial direction. As a result, the circumferential engagement grooves 25 and 26 and the seal members 21 and 22 are in an engaged state in which displacement is possible in the axial direction but displacement is restricted in the circumferential direction.
[0019]
Further, the transition piece 5B is provided with a holding mechanism 27 for holding the side approaching the combustion section 5A to the casing 8. The holding mechanism 27 holds the transition piece 5 </ b> B with respect to the casing 8 such that the transition piece 5 </ b> B can be displaced in the combustion gas flow direction (axial direction along the rotating shaft 6).
[0020]
A positioning mechanism 28 is provided between the transition piece 5 </ b> B and the turbine section 2 to determine the opposing position of the combustion gas outlet 13 and the combustion gas inlet 14. The positioning mechanism 28 includes an end bracket 29 whose one end is pivotally supported on the turbine part 2 side of the transition piece 5B, a positioning pin 30 provided at the other end of the end bracket 29, and a position where the positioning pin 30 is inserted. And a pin hole 31 formed in the casing 1 located at the outer peripheral portion of the first stage stationary blade 9 in other words.
[0021]
A connecting shaft 32 is provided at one end of the end bracket 29, and the connecting shaft 32 is supported by a bearing 33 fixed to the transition piece 5B. The bearing 33 is provided with a fitting hole 34, and a cylindrical eccentric bush 35 is fitted in the fitting hole 34. The eccentric bush 35 is provided with a shaft hole 36 for supporting the connection shaft 32, and the shaft hole 36 has a center that is eccentric in the X dimension from the center of the eccentric bush 35.
[0022]
In the gas turbine equipment having the above-described configuration, the gap between the combustion gas outlet 13 of the transition piece 5B and the combustion gas inlet 14 of the turbine unit 2 due to dimensional change over time is displaced, In some cases, the position of the transition piece 5B is displaced, and the gap is displaced. When such a displacement of the gap occurs, the engagement of the seal members 21 and 22 is not in a proper state, and the wear is accelerated. Therefore, the displacement of the gap must be adjusted. A procedure for adjusting the displacement of the gap will be described with reference to FIG.
[0023]
The holding point of the holding mechanism 27 for holding the side of the transition piece 5B approaching the combustion portion 5A to the casing 8 is point a, the center of the connection shaft 32 held by the eccentric bush 35 is point b, and the combustion gas outlet is provided. 13 is an engagement portion between the outer peripheral edge 17 and the seal member 22, a point c, an inner peripheral edge 16 of the combustion gas outlet 13 and an engagement portion between the seal member 22 is a point d, and the outer peripheral edge 20 of the combustion gas inlet 14 is An engagement point with the seal member 22 is point f, an engagement part between the inner peripheral edge 19 of the combustion gas inlet 14 and the seal member 22 is point e, a pin hole 31 formed on the positioning pin 30 and the casing 8 side. Is defined as point g, each point of the transition piece 5B is represented by squares a, b, c, and d.
[0024]
When the transition piece 5B is displaced like a square a, b, c, and d due to dimensional change over time, the gap L1 is larger than the gap K1, so that the line fe and the line cd are not parallel. In this state, the inner peripheral edge 16 of the combustion gas outlet 13 and the inner peripheral edge 19 of the combustion gas inlet 14 are open. At this time, the engaging portion c of the outer peripheral edge 17 of the combustion gas outlet 13 with respect to the engaging portion f of the outer peripheral edge 20 of the combustion gas inlet 14 is displaced Y1 dimension toward the inner diameter side. The engaging portion d of the inner peripheral edge 16 of the combustion gas outlet 13 with respect to the engaging portion e of the inner peripheral edge 19 of the combustion gas inlet 14 is displaced by Y2 dimension toward the inner diameter side.
[0025]
Therefore, the respective engagement portions of the seal members 21 and 22 are not in a normal engagement state, and one-side contact occurs in the respective axial engagement grooves 23 and 24 and the respective circumferential engagement grooves 25 and 26, resulting in abnormal wear. In a state that causes
[0026]
Then, the eccentric bush 35 having the eccentric amount X is rotated to move the center position of the connecting shaft 32 from the point b to the point b '. By moving the center position of the connection shaft 32 to the point b 'in this way, the combustion gas outlet 13 side of the transition piece 5B can be raised to the outer diameter side, so that the Y1, Y2 dimensions displaced to the inner diameter side are reduced. Alternatively, it can be zero.
[0027]
By displacing the point b to the point b ', the squares a, b, c, and d rotate to the squares a', b ', c', and d '. It moves slightly in the axial direction at the point a '. For this purpose, as described above, the holding mechanism 27 holds the transition piece 5B with respect to the casing 8 so as to be displaceable in the axial direction. Since the inclination of the transition piece 5B on the side of the combustion gas outlet 13 is corrected by rotating the eccentric bush 35, the gaps L1 and K1 are corrected to the gaps L2 and K2. The line fe and the line cd, which were finally in the non-parallel state, become parallel as the line fe and the line c′-d ′, and the sealing members 21 and 22 move in the respective axial directions. The engagement grooves 23 and 24 and the circumferential engagement grooves 25 and 26 are properly engaged.
[0028]
Therefore, abnormal wear due to contact between the seal members 21 and 22 is eliminated, and the life of the seal members 21 and 22 can be extended.
[0029]
From the above, the positioning mechanism 28 serves as adjusting means provided between the transition piece and the turbine portion to adjust the gap between the opposed portions, or the position of the transition piece with respect to the turbine portion. Adjustment means.
[0030]
Next, a second embodiment of the gas turbine equipment according to the present invention will be described with reference to FIGS.
[0031]
In the first embodiment, an adjustment mechanism is provided at a position where the end bracket 29 of the positioning mechanism 28 is pivotally supported by the transition piece 5B. However, in the second embodiment, the tip of the end bracket 29 is provided. An adjustment mechanism was provided in the device.
[0032]
Specifically, a circular fitting hole 29H is provided at the end of the end bracket 29, and an eccentric bush 37 having the same outer diameter as the fitting hole 29H is provided. The eccentric bush 37 has two stoppers 37S protruding in the diametrical direction, and a concave stopper groove 29G for fitting the stopper 37S is provided in a fitting hole 29H of the end bracket 29.
[0033]
On the other hand, the eccentric bush 37 is provided with a pin hole 37H for inserting and fixing the positioning pin 30. The pin hole 37H has a center at a position eccentric from the center of the eccentric bush 37 in the X dimension and a position eccentric in the X dimension from a center line connecting the two stoppers 37S in the diameter direction.
[0034]
Therefore, the eccentric amount X can be adjusted by rotating the eccentric bush 37 by 180 degrees and fitting it in the fitting hole 29H.
[0035]
In the gas turbine equipment having the above-described configuration, when the interval of the gap between the combustion gas outlet 13 of the transition piece 5B and the combustion gas inlet 14 of the turbine unit 2 is changed due to dimensional change over time, or On the other hand, a procedure for adjusting the displacement of the gap when the gap of the gap is displaced by the displacement of the transition piece 5B will be described with reference to FIG.
[0036]
Note that the reference numerals in the figure are the same as those in FIG.
[0037]
When the transition piece 5B is displaced like a square a, b, c, d due to a dimensional change over time, the gap L1 becomes larger than the gap K1, so that the line fe and the line cd do not match. In the parallel state, the inner peripheral edge 16 of the combustion gas outlet 13 and the inner peripheral edge 19 of the combustion gas inlet 14 are open. At this time, the engaging portion c of the outer peripheral edge 17 of the combustion gas outlet 13 with respect to the engaging portion f of the outer peripheral edge 20 of the combustion gas inlet 14 is displaced Y1 dimension toward the inner diameter side. The engaging portion d of the inner peripheral edge 16 of the combustion gas outlet 13 with respect to the engaging portion e of the inner peripheral edge 19 of the combustion gas inlet 14 is displaced by Y2 dimension toward the inner diameter side.
[0038]
Therefore, the respective engagement portions of the seal members 21 and 22 are not in a normal engagement state, and one-side contact occurs in the respective axial engagement grooves 23 and 24 and the respective circumferential engagement grooves 25 and 26, resulting in abnormal wear. In a state that causes
[0039]
Then, the eccentric bush 37 having the eccentric amount X is rotated to move the center position of the positioning pin 30 from the point g to the point g '. By moving the center position of the positioning pin 30 to the point g 'in this way, the combustion gas outlet 13 side of the transition piece 5B can be raised to the outer diameter side, so that Y1 and Y2 displaced to the inner diameter side can be reduced or Can be zero. By displacing the point b to the point b ', the squares a, b, c, and d rotate to the squares a', b ', c', and d '. Since the inclination of the transition piece 5B on the side of the combustion gas outlet 13 is corrected by rotating the positioning pin 30, the gaps L1 and K1 are corrected to the gaps L2 and K2. The line fe and the line cd, which were finally in the non-parallel state, are balanced as the line fe and the line c′-d ′, and the sealing members 21 and 22 are moved in the respective axial directions. The engagement grooves 23 and 24 and the circumferential engagement grooves 25 and 26 are properly engaged.
[0040]
Therefore, abnormal wear due to contact between the seal members 21 and 22 is eliminated, and the life of the seal members 21 and 22 can be extended.
[0041]
Next, a third embodiment of the gas turbine equipment according to the present invention will be described with reference to FIGS.
[0042]
In the present embodiment, a square fitting hole 38 whose two sides are parallel to the radial direction is provided, and a square eccentric bush 39 fitted into the fitting hole 38 is provided. The eccentric bush 39 is provided with a pin hole 38H into which the positioning pin 30 is inserted and fixed. The pin hole 38H has a center eccentric in the X-dimension radial direction from the center where two diagonal lines of the eccentric bush 39 intersect.
[0043]
Therefore, the eccentric amount X can be adjusted by rotating the eccentric bush 39 by 180 degrees and fitting it into the fitting hole 38. As a result, the displacement of the gap between the combustion gas outlet 13 and the combustion gas inlet 14 can be adjusted according to the dimensional change over time as in the second embodiment.
[0044]
Further, according to the present embodiment, the shapes of the fitting hole 38 of the end bracket 29 and the eccentric bush 39 are simpler than in the second embodiment, so that the manufacture is simplified. Further, when the eccentric bush 39 tries to rotate by receiving vibrations or the like during gas combustion, in the second embodiment, the eccentric bush 39 receives a rotational force at the cross section of the two stoppers 37S. For example, since the four faces of the square hole receive the rotational force, the reliability in terms of strength is improved.
[0045]
【The invention's effect】
As described above, according to the present invention, it is possible to obtain a gas turbine facility that can easily repair a change in a gap between a combustion gas outlet of a transition piece and a combustion gas inlet of a turbine portion and prevent early wear of a seal member. Can be.
[Brief description of the drawings]
FIG. 1 is a partially longitudinal side view showing an outline of a gas turbine facility according to the present invention.
FIG. 2 is an enlarged side view showing the periphery of a combustion device and a transition piece of FIG. 1;
FIG. 3 is an external side view showing the transition piece of FIG. 2;
FIG. 4 is a right side view of FIG. 3;
FIG. 5 is a right side view showing a part of the arrangement of the transition pieces of FIG. 2;
FIG. 6 is an enlarged longitudinal cross-sectional view showing a connecting portion between the transition piece and the turbine unit in FIG. 2;
FIG. 7 is an enlarged view showing a transition piece side of the positioning mechanism of FIG. 3;
FIG. 8 is a perspective view showing an eccentric bush used for the positioning mechanism of FIG. 7;
9A and 9B are diagrams illustrating adjustment of displacement of a transition piece, wherein FIG. 9A is a structural diagram, and FIG. 9B is an explanatory diagram.
FIG. 10 is a diagram corresponding to FIG. 6, showing a second embodiment according to the present invention;
FIG. 11 is a perspective view showing the end of the end bracket of FIG. 10;
FIG. 12 is a perspective view showing an eccentric bush used for the end bracket of FIG. 11;
FIG. 13 is a diagram corresponding to FIG. 9B in the second embodiment.
FIG. 14 is a diagram corresponding to FIG. 10 showing a third embodiment according to the present invention.
FIG. 15 is a diagram corresponding to FIG. 11 in the third embodiment.
FIG. 16 is a perspective view showing an eccentric bush used for the end bracket shown in FIG. 15;
[Explanation of symbols]
DESCRIPTION OF SYMBOLS 1 ... Gas turbine equipment, 2 ... Turbine part, 3 ... Compressor, 4 ... Combustion device, 5A ... Combustion part, 5B ... Transition piece, 13 ... Combustion gas outlet, 14 ... Combustion gas inlet, 21, 22 ... Seal member, 28: Positioning mechanism, 29: End bracket, 35, 37, 39: Eccentric bush, K (K1, K2), L (L1, L2): Gap.

Claims (6)

A turbine section, a plurality of combustion devices having a gas combustion section for generating combustion gas and a transition piece for introducing the generated combustion gas to the turbine section, wherein a combustion gas outlet of the transition piece and combustion of the turbine section are provided. A gap is provided at a portion facing the gas inlet, and a seal member for closing the gap is engaged across the combustion gas outlet and the combustion gas inlet. A gas turbine facility, further comprising adjusting means for adjusting a gap between the opposed portions. A turbine section, a plurality of combustion devices having a gas combustion section for generating combustion gas and a transition piece for introducing the generated combustion gas to the turbine section, wherein a combustion gas outlet of the transition piece and combustion of the turbine section are provided. A gap is provided in a portion opposed to the gas inlet, and in a gas turbine facility having a seal member closing the gap straddling the combustion gas outlet and the combustion gas inlet, the position of the transition piece is set to the turbine portion. Gas turbine equipment, characterized in that an adjusting means for adjusting the temperature is provided. One end of the seal member is engaged with the combustion gas outlet in the axial direction of the turbine section, and the other end is engaged with the combustion gas inlet in the radial direction of the turbine section. The gas turbine equipment according to claim 1, wherein: 4. The gas turbine equipment according to claim 1, wherein the adjusting unit is provided in a positioning mechanism that determines a position between the transition piece and the turbine unit. 5. The gas turbine equipment according to claim 4, wherein the positioning mechanism includes an eccentric bush that changes a connection position with the transition piece. The gas turbine equipment according to claim 4, wherein the positioning mechanism includes an eccentric bush that changes a position of the transition piece facing the turbine section.

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