JPH08312963A - Combustor for gas turbine - Google Patents

Abstract

PURPOSE: To improve the strength of a ceramic liner and to improve the productivity in the combustor for a gas turbine having the liner. CONSTITUTION: This combustor for a gas turbine has a ceramic liner 1 formed in a cylindrical shape for partitioning a combustion chamber 11 and a metal dome 2 formed in a bowl shape coupled to the base end side of the liner 1, and comprises a liner collar 12 annularly protruding from the base end of the line 1, a dome collar 22 annularly protruding from the end of the dome 2, and a band 6 so having a V-shaped section as to draw the collar 12 and the collar 22 to each other.

Description

Detailed Description of the Invention

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to an improvement in a gas turbine combustor having a ceramic liner.

[0002]

2. Description of the Related Art In a gas turbine in which a liner (combustion cylinder) used in a high temperature atmosphere is formed of a ceramic material, it is necessary to avoid stress concentration on the brittle ceramic material.

A conventional gas turbine combustor, for example, is shown in FIG. 10 (Japanese Patent Laid-Open No. 56-745).
28, gazette).

To explain this, a combustor of a gas turbine has a cylindrical ceramic liner 51 that defines a combustion chamber 50, and a bowl-shaped ceramic dome 52 connected to the base end side of the liner 51. With.

As shown in FIG. 11, the tip flange portion 53 of the dome 52 is fitted to the inner peripheral surface of the liner 51, and the both are fastened via a plurality of metal clamps 54.

Holes 55 and 56 are formed in the tip flange portion 53 of the dome 52 and the liner 51 by machining. The dome 52 is inserted through the pins 56 inserted into the holes 55 and 56.
The rotation of the liner 51 with respect to is locked.

During operation of the gas turbine, since the dome 52 and the liner 51 are used in a high temperature atmosphere, a difference in thermal expansion occurs between the members, and the clamps 54 are elastic to the difference in thermal expansion. It is supposed to deform.

[0008]

However, in such a conventional gas turbine combustor, the dome 5 is used.
Since stress concentrates on the holes 55 and 56 formed by machining in the second tip flange portion 53 and the liner 51, it is difficult to secure sufficient strength.

Further, machining the ceramic material causes a large increase in production cost.

Since the thickness of the ceramic dome 52 is greatly changed at the tip flange portion 53, the dome 52
It is difficult to increase productivity because cracking and deformation are likely to occur during molding and firing.

An object of the present invention is to solve the above problems and to improve the strength of the liner and the productivity of the gas turbine combustor provided with the ceramic liner.

[0012]

A combustor for a gas turbine according to claim 1 has a cylindrical ceramic liner defining a combustion chamber, and a bowl shape connected to a base end portion of the liner. In a gas turbine combustor including a metal dome, a liner collar portion that annularly projects from a base end portion of the liner, a dome collar portion that annularly projects from a tip portion of the dome, a liner collar portion and a dome collar. A band having a V-shaped cross section so as to draw the parts toward each other.

According to a second aspect of the present invention, in the gas turbine combustor according to the first aspect of the invention, the orthogonal engagement surface that engages with the band of the liner collar is a plane orthogonal to the center line of the liner. And a slanted engagement surface that engages with the band of the dome flange is formed in a conical surface that is slanted with respect to the centerline of the liner.

A gas turbine combustor according to a third aspect of the present invention is the gas turbine combustor according to the first or second aspect of the present invention, wherein a cushioning material made of ceramic fiber is interposed between the orthogonal engagement surface of the liner collar portion and the band. To wear.

A combustor for a gas turbine according to a fourth aspect of the present invention is the combustor according to any one of the first to third aspects, wherein a cushioning material in which a ceramic fiber is woven between the liner collar portion and the dome collar portion is used. Intervene.

According to a fifth aspect of the present invention, in the gas turbine combustor according to any one of the first to fourth aspects, an arc shape is formed so that the band is pressed against the orthogonal engagement surface of the liner collar portion. Forming a protruding annular protrusion having a cross section of.

A gas turbine combustor according to a sixth aspect of the present invention is the gas turbine combustor according to any one of the first to fifth aspects, in which a sealing surface that joins the liner collar of the dome collar has a center line of the liner. Formed in a plane orthogonal to
A curved corner having an arcuate cross section is formed on at least one of the inner and outer circumferences of the sealing surface.

According to a seventh aspect of the present invention, in the gas turbine combustor according to any one of the first to sixth aspects, the band is surrounded by the liner collar portion and the dome collar portion over substantially the entire circumference. It is formed in a C shape and has a spring that draws the abutment ends of the band toward each other.

[0019]

In the gas turbine combustor according to claim 1, the dome collar portion and the liner collar portion engaging with the band having a V-shaped cross section are pulled toward each other by urging the band in the radial direction. To be As a result, no gap is formed at the joint between the two, and the sealing property of the combustion chamber is ensured.

During operation of the gas turbine, since the dome and the liner are used in a high temperature atmosphere, a difference in thermal expansion of the liner with respect to the dome occurs, but this thermal expansion difference causes relative displacement between the dome and the liner via the band. Absorbed by. As a result, it is possible to prevent permanent deformation of the metal dome and the like, and it is also possible to prevent stress concentration on the ceramic liner and damage.

Since the ceramic liner is formed in a simple tubular shape to reduce the number of parts to be machined and to prevent the sectional shape from changing rapidly, stress concentration occurs during operation of the gas turbine. This will prevent damage and damage to the liner, simplify the molding of the liner, and prevent cracks and deformation during molding and firing of the liner, thus improving productivity and reducing product costs. .

In the combustor of the gas turbine according to the present invention, since the orthogonal engagement surface for engaging the band of the liner collar portion is formed in a plane shape orthogonal to the center line of the liner, it is made of metal. Due to the difference in thermal expansion between the dome and the ceramic liner, even if the band that engages with the inclined engagement surface of the dome collar expands in diameter, the orthogonal disc portion of the band should be separated from the orthogonal engagement surface of the liner collar. No parallel displacement. For this reason, no gap is formed at the joint between the respective sealing surfaces, the hermeticity of the combustion chamber is ensured, and it is possible to prevent the dome collar and the liner collar from colliding with each other and causing damage.

In the combustor of the gas turbine according to the present invention, a cushioning material made of ceramic fibers is interposed between the band and the orthogonal engagement surface of the liner collar portion, whereby the ceramic liner collar portion is It is possible to prevent stress concentration at the corners and damage.

In the combustor of the gas turbine according to the present invention, a cushioning material formed by knitting ceramic fibers is interposed between the liner collar portion and the dome collar portion, whereby a corner portion of the ceramic liner collar portion is provided. It is possible to prevent stress concentration from causing damage.

In the combustor for a gas turbine according to a fifth aspect of the present invention, the corner of the ceramic liner collar is formed by pressing an annular protrusion protruding from the band with an arcuate cross section against the orthogonal engagement surface of the liner collar. It is possible to prevent stress from concentrating on the part and causing damage. As a result, it is not necessary to provide a cushioning material between the orthogonal engaging surfaces of the annular protrusion and the liner collar, and the strength of the ceramic liner can be sufficiently secured.

In the gas turbine combustor according to the sixth aspect of the present invention, the sealing surface having a curved corner portion having an arcuate cross section is pressed against the liner collar portion, whereby the ceramic liner collar portion is cornered. Prevents stress concentration from causing damage. As a result, it is not necessary to provide a cushioning material between the sealing surface of the dome flange and the liner flange, and the strength of the ceramic liner can be sufficiently ensured.

In the combustor of the gas turbine according to claim 7, the elastic restoring force of the spring draws the abutting ends of the bands toward each other, and the bands are urged in the diameter reducing direction, so that the V-shaped cross section is obtained. The dome collar and the liner collar that engage the curved band are drawn together.
As a result, no gap is formed at the joint between the two, and the sealing property of the combustion chamber is ensured.

[0028]

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

As shown in FIG. 1, a combustor of a gas turbine comprises a cylindrical ceramic liner 1 defining a combustion chamber 11, and a bowl-shaped metal liner connected to the proximal end of the liner 1. And a dome 2.

A swirler 3 having a cylindrical shape on the base end side of the dome 2.
Is connected. The intake air pressure-fed from a compressor (not shown) passes through the heat exchanger, then is guided to the swirler 3 through the flow passages defined outside the liner 1 and the dome 2, and from each slit 7 opened in the swirler 3. Combustion chamber 11
Inflow while turning to.

A fuel injection valve 9 is arranged inside the swirler 3. The fuel injected from the fuel injection valve 9 into the combustion chamber 11 mixes with the intake air introduced from the swirler 3 to form a diffusion flame.

The base end (not shown) of the swirler 3 is fixedly coupled to the engine casing via bolts or the like.

The liner 1 is formed in a right cylinder shape, and a plurality of dilution air ports 19 are opened in the middle thereof. The tip outer peripheral surface 13 of the liner 1 is fitted into the transition piece 8. The gas burned in the combustion chamber 11 is guided to a turbine (not shown) through the transition piece 8 and rotationally drives the turbine.

The base end of the liner 1 and the tip of the dome 2 are
It is fastened through a C-shaped metal band 6.

As shown in FIG. 2, the band 6 includes a liner 1
Of the liner 1, an inclined disc portion 32 inclined with respect to the center line L of the liner 1, and a cylindrical portion 33 connecting the orthogonal disc portion 31 and the inclined disc portion 32.

At the base end of the ceramic liner 1, a collar portion 12 having an L-shaped cross section and projecting annularly is integrally formed. The collar portion 12 has a flat seal surface 14 orthogonal to the center line L of the liner 1 and an orthogonal engagement surface 15.

A brim portion 22 having an L-shaped cross section and projecting in an annular shape is integrally formed at the tip of the metal dome 2.
The collar portion 22 has a flat sealing surface 24 that is orthogonal to the center line L of the liner 1 and a conical inclined surface 25 that is inclined with respect to the center line L.

The orthogonal disc portion 31 of the band 6 and the orthogonal engagement surface 15 of the liner collar portion 12 face each other in parallel, and a disc-shaped cushioning material 17 is interposed between the two.

The seal surface 14 of the liner collar portion 12 and the seal surface 24 of the dome collar portion 22 face each other in parallel, and a disc-shaped cushioning material 18 is interposed between the two.

An annular protrusion 16 is provided on the inner periphery of the orthogonal engaging surface 15.
Are integrally formed. A cushioning material 18 is provided on the outer side of the annular protrusion 16.
By being fitted, the cushioning member 18 is positioned in the radial direction. The amount of protrusion of the annular protruding portion 16 is
Less than the thickness of.

The cushioning materials 17 and 18 are knitted ceramic fibers, and the thickness of the cushioning materials 17 and 18 is greatly changed by elastically deforming the ceramic fibers.

As shown in FIGS. 4 and 5, a pair of flanges 41 and 42 are fixed to the abutting end of the C-shaped band 6. A bolt 43 is provided to insert the flanges 41 and 42, and a spring 44 is provided to draw the flanges 41 and 42 toward each other via the bolt 43.

With the above construction, the operation will be described below.

The flanges 41 and 42 of the band 6 are attracted by the elastic restoring force of the spring 44 to reduce the diameter of the band 6, and the orthogonal disc portion 31 of the band 6 is pressed against the orthogonal engagement surface 15 of the liner collar portion 12. And the inclined disc portion 32 is attached to the inclined engagement surface 2 of the dome collar portion 22.
Pressed on 5.

Since the slanted disc portion 32 of the band 6 and the slanted engagement surface 25 of the dome collar portion 22 are slanted with respect to the liner center line L, the diameter of the band 6 is reduced via the spring 44, and the dome is reduced. An axial force is applied to press the sealing surface 24 of the collar portion 22 against the sealing surface 14 of the liner collar portion 12 via the cushioning material 18. Due to this axial biasing force, no gap is formed at the joint between the sealing surfaces 14 and 24, and the hermeticity of the combustion chamber 11 is ensured.

During operation of the gas turbine, since the dome 2 and the liner 1 are used in a high temperature atmosphere, a difference in thermal expansion of the liner 1 with respect to the dome 2 occurs. Are absorbed by relative displacement. As a result, it is possible to prevent permanent deformation of the metal dome 2 and the like, and it is possible to prevent stress concentration on the ceramic liner 1 and damage.

Since the orthogonal disc portion 31 of the band 6 and the orthogonal engagement surface 15 of the liner collar portion 12 are formed in a plane shape orthogonal to the liner center line L, as shown in FIG.
When the band 6 is expanded due to the difference in thermal expansion between the metal dome 2 and the ceramic liner 1, the orthogonal disc portion 31 of the band 6 is displaced in parallel to the orthogonal engagement surface 15 of the liner collar portion 12 without being separated. Therefore, each sealing surface 14, 24
There is no gap in the joint portion, the sealing property of the combustion chamber 11 is secured, and it is possible to prevent the dome collar portion 22 and the liner collar portion 12 from colliding with each other and causing damage.

On the other hand, as shown in FIG. 6, the band 6 has two inclined disk portions 32 facing each other, and the diameter of the band 6 is reduced via the spring 44, so that the dome flange portion 22 and In the case of the structure in which the liner flange portion 12 is drawn to join the sealing surfaces 14 and 24, as shown in FIG. 7, when the band 6 is expanded due to the difference in thermal expansion between the metal dome 2 and the ceramic liner 1, the band 6 Since the inclined disc portion 34 of 6 is separated from the engagement surface 19 of the liner collar portion 12, a gap is formed at the joint portion between the respective sealing surfaces 14 and 24.

A disc-shaped cushioning material 17 is interposed between the orthogonal disc portion 31 of the band 6 and the orthogonal engagement surface 15 of the liner collar portion 12, whereby the ceramic liner collar portion 12 is formed.
Concentration of stress on the corners 15a and 15b of the orthogonal engaging surface 15 is relieved.

A disk-shaped cushioning material 1 between the sealing surface 14 of the liner collar 12 and the sealing surface 24 of the dome collar 22.
8 is interposed so that the ceramic liner collar portion 1
The concentration of stress on the corners 14a and 14b of the second sealing surface 14 is relieved.

The ceramic liner 1 is formed in a cylindrical shape which is axially symmetric with respect to the center line L, has a uniform thickness, is not machined, and has a portion whose cross-sectional shape changes rapidly. Since it does not exist, it is possible to prevent stress concentration from occurring during operation of the gas turbine, resulting in damage.

Further, since the ceramic liner 1 is formed in a cylindrical shape having a uniform wall thickness, cracking and deformation are suppressed from occurring during the molding and firing of the liner 1, and the productivity is improved, and the product is improved. The cost can be reduced.

Next, another embodiment shown in FIG. 8 will be described. It should be noted that the same parts as those in FIG.

The C-shaped metal band 6 for fastening the liner collar portion 12 and the dome collar portion 22 has an orthogonal disc portion 1 orthogonal to the center line of the liner 1 and an inclination with respect to the center line of the liner 1. It has an inclined disc portion 32, and a cylindrical portion 33 connecting the orthogonal disc portion 31 and the inclined disc portion 32.

On the orthogonal disc portion 31, an annular projection portion 36 which is annularly raised toward the orthogonal engagement surface 15 of the liner collar portion 12 is integrally formed. The annular protrusion 36 is formed so that its cross section is curved in an arc shape.

The seal surface 14 of the liner collar portion 12 and the seal surface 24 of the dome collar portion 22 face each other in parallel, and a disc-shaped cushioning material 18 is interposed between them.

With the above construction, the operation will be described below.

The flanges 41 and 42 of the band 6 are attracted by the elastic restoring force of the spring 44 to reduce the diameter of the band 6, and the annular projection 36 of the band 6 is pressed against the orthogonal engagement surface 15 of the liner flange 12. And the inclined disc portion 32 is attached to the inclined engagement surface 2 of the dome collar portion 22.
It is pressed against 5, and no gap is left at the joint between the sealing surfaces 14 and 24, so that the sealing performance of the combustion chamber 11 is ensured.

Since the annular projection 36 of the band 6 is formed so that its cross section is curved in an arc shape, the corner 15a of the orthogonal engaging surface 15 of the ceramic liner collar 12 is formed.
The concentration of stress on 15b is relieved. As a result,
Since it is not necessary to provide a cushioning material between the annular projection 36 and the orthogonal engagement surface 15 of the liner collar 12, the ceramic liner 1
Sufficient strength can be secured.

A disk-shaped cushioning material 1 between the sealing surface 14 of the liner collar 12 and the sealing surface 24 of the dome collar 22.
8 is interposed so that the ceramic liner collar portion 1
The concentration of stress on the corners 14a and 14b of the second sealing surface 14 is relieved.

Next, another embodiment shown in FIG. 9 will be described. It should be noted that the same parts as those in FIG.

The metal dome collar portion 22 has a sealing surface 28 which is orthogonal to the center line of the liner 1. The sealing surface 28 has corners 28a and 28b, respectively, whose inner peripheral end and outer peripheral end are curved in an arc shape in cross section.

Similar to the above embodiment, the orthogonal disc portion 31 is integrally formed with an annular projection portion 36 which is annularly raised toward the orthogonal engagement surface 15 of the liner collar portion 12. Annular protrusion 36
Is formed so that its cross section is curved in an arc shape.

With the above construction, the operation will be described below.

The respective flanges 41, 42 of the band 6 are attracted by the elastic restoring force of the spring 44 to reduce the diameter of the band 6, and the annular projection 36 of the band 6 is pressed against the orthogonal engagement surface 15 of the liner collar 12. And the inclined disc portion 32 is attached to the inclined engagement surface 2 of the dome collar portion 22.
5, the sealing surfaces of the combustion chambers 11 are ensured without any gaps in the joints between the sealing surfaces 14 and 28.

Sealing surface 28 of metal dome collar 22
Is that since the corners 28a, 28b of the inner and outer peripheral ends joined to the sealing surface 14 of the ceramic liner collar 12 are curved in a circular arc shape, the concentration of stress on the sealing surface 14 is alleviated. It As a result, both sealing surfaces 14, 2
It is not necessary to provide a cushioning material between 8 and the ceramic liner 1 can have sufficient strength.

[0067]

As described above, in the combustor of the gas turbine according to the first aspect of the present invention, the dome collar portion and the liner collar portion are attracted to each other through the band having the V-shaped cross section, so that the combustion chamber As well as ensuring hermeticity,
The ceramic liner has a simple cylindrical shape to improve productivity and reduce the cost of the product.

In the combustor of the gas turbine according to the present invention, the orthogonal engaging surface for engaging the band of the liner collar portion is formed in a plane shape orthogonal to the center line of the liner. Due to the difference in thermal expansion between the dome and the ceramic liner, even if the outer diameter of the metal dome expands significantly, it is possible to prevent gaps in the joints between the sealing surfaces, and ensure the sealability of the combustion chamber. It is possible to prevent the dome collar portion and the liner collar portion from colliding with each other and causing damage.

In the combustor of the gas turbine according to the third aspect of the present invention, since the cushioning material woven with the ceramic fiber is interposed between the band and the orthogonal engagement surface of the liner collar portion, the ceramic liner collar portion is provided. It is possible to prevent stress concentration at the corners and damage.

In the combustor of the gas turbine according to the present invention, since the cushioning material made of ceramic fibers is interposed between the liner collar portion and the dome collar portion, the ceramic liner collar portion has a corner portion. It is possible to prevent stress concentration from causing damage.

In the combustor of the gas turbine according to the fifth aspect of the present invention, since the annular projection protruding from the band with an arcuate cross section is pressed against the orthogonal engagement surface of the liner collar, the corner portion of the ceramic liner collar is pressed. It is possible to prevent damage from being caused by stress concentration on the. As a result, it is not necessary to provide a cushioning material between the orthogonal engaging surfaces of the annular protrusion and the liner collar, and the cost of the product can be reduced.

In the combustor of the gas turbine according to the sixth aspect, since the sealing surface having a curved corner having an arcuate cross section is pressed against the liner collar, stress is applied to the corner of the ceramic liner collar. It is possible to prevent concentration and damage. As a result, it is not necessary to provide a cushioning material between the sealing surface of the dome collar portion and the liner collar portion, and the cost of the product can be reduced.

In the combustor for a gas turbine according to a seventh aspect, the elastic restoring force of the spring draws the abutment ends of the bands toward each other, and the bands are urged in the radial direction, so that the V-shaped cross section is obtained. The dome collar and the liner collar that engage the curved band are drawn together. As a result, no gap is formed at the joint between the two, and the sealing property of the combustion chamber is ensured.

[Brief description of drawings]

FIG. 1 is a sectional view of a combustor showing an embodiment of the present invention.

FIG. 2 is a cross-sectional view of a liner and dome coupling portion.

FIG. 3 is a sectional view of the liner and dome joint portion during thermal expansion.

FIG. 4 is a front view of the same combustor.

FIG. 5 is a front view of the same band.

FIG. 6 is a cross-sectional view of a liner / dome coupling portion according to another embodiment.

FIG. 7 is a cross-sectional view of the joint portion between the liner and the dome during thermal expansion.

FIG. 8 is a cross-sectional view of a liner-dome coupling portion according to still another embodiment.

FIG. 9 is a cross-sectional view of a liner-dome coupling portion according to still another embodiment.

FIG. 10 is a sectional view of a combustor showing a conventional example.

FIG. 11 is an enlarged cross-sectional view of portion A of FIG.

[Explanation of symbols]

 DESCRIPTION OF SYMBOLS 1 liner 2 dome 6 band 11 combustion chamber 12 liner collar 14 sealing surface 15 orthogonal engagement surface 17 cushioning material 18 cushioning material 22 dome collar 24 sealing surface 25 inclined engagement surface 28 sealing surface 28a corner 28b corner 31 orthogonal Disc part 32 Inclined disc part 36 Annular protrusion part 44 Spring

Claims (7)

[Claims] 1. A gas turbine combustor comprising: a cylindrical ceramic liner defining a combustion chamber; and a bowl-shaped metal dome connected to the base end of the liner. A liner collar projecting annularly from the base end, a dome collar projecting annularly from the tip of the dome, and a band having a V-shaped cross section so as to draw the liner collar and the dome collar together. Combustor of gas turbine characterized by 2. An orthogonal engaging surface that engages with the band of the liner flange is formed in a plane shape orthogonal to the center line of the liner, and an inclined engaging surface that engages with the band of the dome flange is liner. The combustor of the gas turbine according to claim 1, wherein the combustor is formed in a conical surface inclined with respect to a center line of the gas turbine. 3. A combustor for a gas turbine according to claim 1, wherein a cushioning material woven with ceramic fibers is interposed between the orthogonal engagement surface of the liner collar portion and the band. 4. A combustor for a gas turbine according to claim 1, wherein a cushioning material made of ceramic fibers is interposed between the liner collar portion and the dome collar portion. . 5. The ring-shaped protruding portion having an arcuate cross-section is formed on the band so as to be pressed against the orthogonal engaging surface of the liner collar portion, and the band-shaped protruding portion is formed. A combustor of the described gas turbine. 6. A seal surface, which is joined to the liner collar portion of the dome collar portion, is formed in a plane shape orthogonal to a center line of the liner, and at least one of inner and outer circumferences of the seal surface has an arc-shaped cross section. 2. A curved corner is formed.
5. A combustor for a gas turbine according to any one of items 1 to 5. 7. The band is formed in a C shape that surrounds the liner collar portion and the dome collar portion over substantially the entire circumference, and is provided with a spring that draws the abutment end portions of the band toward each other. A combustor for a gas turbine according to any one of items 1 to 6.