JP2008151007A - Turbine blade ring structure and its assembling method - Google Patents

Abstract

<P>PROBLEM TO BE SOLVED: To provide a turbine blade ring structure, easy in assembling, and capable of successively installing a seal member. <P>SOLUTION: This turbine blade ring structure has a first stage upstream side heat shielding ring 29, a first stage downstream side heat shielding ring 31 arranged at an interval on the downstream side in the axial direction of a first stage blade ring 27 from the first stage upstream side heat shielding ring 29, a first stage divided ring 33 divided into a plurality in the peripheral direction of the first stage blade ring 27, supported by the first stage upstream side heat shielding ring 29 and the first stage downstream side heat shielding ring 31 and holding a clearance with a first stage moving blade 13, and a first stage fixed ring 35 divided into a plurality in the peripheral direction, respectively pressing the first stage downstream side heat shielding ring 31 to the upstream side in the axial direction and fixed to the first stage blade ring 27. The whole insertion object sides are opened toward the downstream side in the axial direction on mutual fitting parts of the first stage blade ring 27, the first stage upstream side heat shielding ring 29, the first stage divided ring 33, the first stage downstream side heat shielding ring 31 and the first stage fixed ring 35 except for a fitting part to the first stage blade ring 27 of at least the first stage upstream side heat shielding ring 29. <P>COPYRIGHT: (C)2008,JPO&INPIT

Description

  The present invention relates to a turbine blade ring structure and an assembling method thereof.

The gas turbine obtains power by expanding the combustion gas of the combustor with the turbine, and high-temperature combustion gas is supplied to the inlet side of the turbine. A predetermined clearance is set between the turbine rotor blade and the turbine blade ring, and the turbine rotor blade is designed to obtain the rotational force of the turbine rotor efficiently.
Since high-temperature combustion gas is supplied to the inlet side of the turbine, the turbine blade ring side is provided with a plurality of heat shield rings divided in the circumferential direction so that the influence of thermal deformation does not reach the clearance setting as much as possible. The heat shield ring supports an inner wall that faces the tip of the turbine rotor blade and is divided into a plurality of parts in the circumferential direction (see, for example, Patent Document 1).

Cooling air is supplied to the split ring from the turbine blade ring side, and the split ring is appropriately cooled to suppress the influence of thermal deformation.
A seal member extending in the circumferential direction is interposed between the fitting portions of the turbine blade ring, the heat shield ring, and the split ring, thereby preventing cooling air from leaking.
The thing shown by patent document 1 is comprised so that a downstream heat insulation ring may be divided | segmented into plurality, and it may be hold | maintained at a turbine blade ring by the pressing piece which comprises the most downstream side.

JP 2004-150325 A

However, the one shown in Patent Document 1 is such that a convex portion provided on the presser piece side is fitted into a concave portion provided on the turbine blade ring side on the upstream side in the axial direction of the fitting portion between the presser piece and the turbine blade ring. Since it is comprised so that it may match | combine, both cannot be fitted by moving a presser piece to an axial direction. For this reason, it is necessary to insert and assemble each divided portion of the heat shield ring including at least the presser piece in the circumferential direction.
In order to insert and assemble each divided portion of the heat shield ring in the circumferential direction, there is a problem that the assembly is difficult, for example, it is impossible to assemble because there is a slight distortion in the shape.
In addition, since the seal member that extends in the circumferential direction is inserted after the heat shield ring is assembled, the surface is damaged by the seal member coming into contact with the heat shield ring or the like. There is a problem that it is easy to enter and causes a seal failure.

  In view of the above circumstances, an object of the present invention is to provide a turbine blade ring structure that is easy to assemble and that allows sequential mounting of a seal member, and a method for assembling a turbine blade ring structure using the turbine blade ring structure.

In order to solve the above problems, the present invention provides the following means.
A turbine blade ring structure according to the present invention includes a first heat shield ring that is divided into a plurality of portions in the circumferential direction and is supported by the turbine blade ring, and an axial downstream of the turbine blade ring from the first heat shield ring. A second heat shield ring arranged on the side and spaced apart and divided into a plurality in the circumferential direction and supported by the turbine blade ring, and divided into a plurality in the circumferential direction of the turbine blade ring and the first A split ring that is supported by the heat shield ring and the second heat shield ring and maintains a clearance with the moving blade, and divided into a plurality of portions in the circumferential direction, each of the second heat shield rings on the upstream side in the axial direction A fixed ring that presses and is fixed to the turbine blade ring, and at least the turbine blade ring and the first heat shield ring excluding a fitting portion of the first heat shield ring to the turbine blade ring A fitting portion of the split ring, the second heat shield ring and the fixing ring. Characterized in that the insertion side is open toward the downstream side of the axial direction.

The turbine blade ring structure according to the present invention includes at least a turbine blade ring, a first heat shield ring, a split ring, a second heat shield ring, and a fixed portion excluding a fitting portion of the first heat shield ring to the turbine blade ring. The insertion side of the mutual fitting parts of the rings is opened toward the downstream side in the axial direction. In other words, the insertion side of the fitting part has a constant cross-sectional area along the radial direction or goes to the downstream side. After the first heat shield ring is attached to the turbine blade ring, there is no portion where the cross-sectional area along the radial direction is larger on the upstream side than on the downstream side. The split ring, the second heat shield ring, and the fixing ring can be incorporated from the downstream side to the upstream side along the axial direction along the respective fitting surfaces.
And since a fixing ring is fixed to a turbine blade ring and an assembly is completed, an assembly is easy and can be performed in a short time.
Further, for example, when a seal member extending in the circumferential direction is attached to the fitting portion between the split ring and the second heat shield ring, the seal member is moved in the axial direction after the split ring is assembled. Assembly, then the second heat shield ring can be assembled in the axial direction.
Thus, since the seal member can be assembled in the axial direction, the seal member can be prevented from moving in contact with other members during assembly. Thereby, since the surface of the sealing member is not damaged, it is possible to prevent deterioration of the sealing performance of the sealing member.
Note that “excluding at least the fitting portion of the first heat shield ring to the turbine blade ring” is applied to the fitting portion, and the fitting portion of the first heat shield ring to the turbine blade ring is as follows. It does not specify that the insertion side is not opened toward the downstream side in the axial direction.

  Further, in the turbine blade ring structure according to the present invention, the fitting portion between the turbine blade ring and the fixed ring has an annular convex portion in which one of the circumferential directions protrudes toward the other and the other on the other. An annular concave portion into which the annular convex portion is fitted is provided.

As described above, the fitting portion between the turbine blade ring and the fixed ring includes an annular convex portion in which one of the circumferential directions protrudes toward the other, and an annular concave portion into which the annular convex portion is fitted on the other. Therefore, the radial position between the turbine blade ring and the fixed ring can be defined by engaging the annular convex portion and the annular concave portion.
Since the fixing ring position can be specified if both radial positions can be defined, the radial positions of the second heat shield ring and the split ring can be positioned at predetermined positions.

  Further, in the turbine blade ring structure according to the present invention, at the downstream end portion of the fitting portion between the fixed ring and the second heat shield ring, a part in one circumferential direction protrudes toward the other. And a concave portion into which the convex portion is fitted.

In this way, at the downstream end of the fitting portion between the fixing ring and the second heat shield ring, a convex portion in which one of the circumferential directions protrudes toward the other and the convex portion on the other. Since the concave portion to be fitted is provided, the circumferential position between the fixing ring and the second heat shield ring can be defined by the engagement between the convex portion and the concave portion.
If the circumferential position of both can be defined, the fixing ring is attached to the turbine blade ring with, for example, a bolt, and the position can be specified. Therefore, the circumferential position of the second heat shield ring is positioned at a predetermined position. be able to.

  In the turbine blade ring structure according to the present invention, at the upstream end portion of the fitting portion between the split ring and the second heat shield ring, one of the circumferential directions protrudes toward the other. And a concave portion into which the convex portion is fitted.

Thus, at the upstream end portion of the fitting portion between the split ring and the second heat shield ring, a convex portion in which one of the circumferential directions protrudes toward the other and the convex portion on the other side. Since the fitting recess is provided, the circumferential position between the split ring and the second heat shield ring can be defined by the engagement between the projection and the recess.
In this case, by setting either one to a predetermined position, the other can be positioned to a predetermined position.
That is, for example, if the second heat shield ring can be positioned by the fixing ring, the position of the split ring can be positioned at a predetermined position.

  In addition, a method for assembling a turbine blade ring structure according to the present invention includes a first heat shield ring divided into a plurality of portions in the circumferential direction and supported by the turbine blade ring, and the turbine blade ring from the first heat shield ring. And a second heat shield ring that is divided into a plurality of portions in the circumferential direction and supported by the turbine blade ring, and is divided into a plurality of portions in the circumferential direction of the turbine blade ring. A split ring that is supported by the first heat shield ring and the second heat shield ring and maintains a clearance with the moving blade, and divided into a plurality in the circumferential direction, each of the second heat shield rings being in the axial direction A stationary ring that is pressed to the upstream side of the turbine and fixed to the turbine blade ring. The turbine blade ring as the assembly member, the first heat shield ring, the split ring, and the second heat shield ring. And fitting of at least the first heat shield ring of the fixing ring to the turbine blade ring A method for assembling a turbine blade ring structure in which the inserted side is opened toward the downstream side in the axial direction with respect to the mutual fitting portions except the portion, and the first heat shield ring is attached to the turbine blade ring After that, the split ring, the second heat shield ring, and the fixing ring are assembled in an axial direction along the respective fitting surfaces, and the fixing ring is fixed to the turbine blade ring and assembled. In the case where there is a seal member extending in the circumferential direction at the part, the seal member is attached to the previous assembly member from the axial direction, and then the next assembly member is attached.

In the assembling method of the turbine blade ring structure according to the present invention, after the first heat shield ring is attached to the turbine blade ring, the split ring, the second heat shield ring, and the fixing ring are respectively disposed along the mutual fitting surfaces. Since the assembly is completed by assembling from the downstream side to the upstream side along the axial direction and fixing the fixing ring to the turbine blade ring, the assembly is easy and can be performed in a short time.
In addition, when mounting a sealing member extending in the circumferential direction on the fitting portion between the assembly members, after assembling the previous assembly member, the seal member is assembled in the axial direction, and then the subsequent assembly member is attached. Since it is assembled in the axial direction, the seal member can be prevented from moving in contact with other members during assembly.
Thereby, since the surface of the sealing member is not damaged, it is possible to prevent deterioration of the sealing performance of the sealing member.
Note that “excluding at least the fitting portion of the first heat shield ring to the turbine blade ring” is applied to the fitting portion, and the fitting portion of the first heat shield ring to the turbine blade ring is as follows. It does not specify that the insertion side is not opened toward the downstream side in the axial direction.

In the present invention, the mutual fitting portions of the turbine blade ring, the first heat shield ring, the split ring, the second heat shield ring, and the fixed ring excluding the fitting portion of the first heat shield ring to the turbine blade ring Since the insertion side is opened toward the downstream side in the axial direction, the assembly is easy and can be performed in a short time.
In addition, when a seal member extending in the circumferential direction is attached to the fitting portion, the seal member can be assembled in the axial direction, so that the seal member is prevented from moving in contact with other members during assembly. It is possible to prevent deterioration of the sealing performance of the sealing member.
In addition, the structure by which the to-be-inserted side is open | released toward the downstream of the axial direction is also included about the fitting part to the turbine blade ring of a 1st heat shield ring.

Next, an embodiment of the present invention will be described with reference to FIGS.
FIG. 1 is a longitudinal sectional view partially showing a schematic configuration of an inlet portion of a gas turbine 1 having a turbine blade ring structure according to the present embodiment.
Inside the gas turbine 1, a stationary blade provided on the stationary side around the rotor (not shown) and a moving blade attached on the rotor side form a pair to form a stage. A plurality of stages are arranged in the axial direction of the rotor (left and right direction in FIG. 1).
A combustion gas flow path 3 that passes through these moving blades and stationary blades is formed.
In FIG. 1, the first stage 5 and the second stage 7 from the upstream side where the combustion gas flows are illustrated, but actually, the third stage, the fourth stage,... It has a multistage structure that follows.

The first stage 5 includes a first stage stationary blade 9, a first stage blade ring structure (turbine blade ring structure) 11 that holds the first stage stationary blade 9, and a first stage moving blade 13.
The second stage 7 includes a second stage stationary blade 15, a second stage blade ring structure (turbine blade ring structure) 17 that holds the second stage stationary blade 15, and a second stage moving blade 19.
A large number of stationary blades such as the first stage stationary blade 9 and the second stage stationary blade 15 are arranged radially and are held by ring-shaped partition plate outer rings 21 and 22 and ring-shaped partition plate inner rings 23 and 24. These stationary blades act to expand the combustion gas in the combustion gas flow path 3 to generate velocity energy, and to change the flow direction to create a momentum in the rotational direction of the shaft.

A large number of moving blades such as the first-stage moving blade 13 and the second-stage moving blade 19 are arranged radially, and are firmly attached to the outer periphery of a disk 25 provided in a cylindrical shape so as to protrude from the rotor. The rotor blades act to absorb the combustion gas energy converted into velocity energy by the stationary blades and convert it into the rotational energy of the rotor.
The gas turbine 1 performs work such as, for example, turning a generator connected to the rotor to generate electric power using the rotational energy.

The configuration of the first stage 5 will be described with reference to FIGS.
FIG. 2 is a partially enlarged cross-sectional view showing an enlarged main part of the first stage blade ring structure 11. 3 and 4 are partially enlarged views showing the X view of FIG.
The first stage blade ring structure 11 includes a first stage blade ring (turbine blade ring) 27, a first stage upstream side heat shield ring (first heat shield ring) 29, and a first stage downstream side heat shield ring. (Second heat shield ring) 31, first stage split ring (partition ring) 33, first stage fixing ring (fixing ring) 35, attachment member 37, and impingement plate 39 are provided. .

The first stage blade ring 27 is formed by casting, for example, and includes a cylindrical space in which the first stage rotor blade 13 can be accommodated, and constitutes a casing of the gas turbine 1.
The first stage upstream side heat shield ring 29 is an annular part, and is fixed to the inside of the first stage blade ring 27 at the outer peripheral portion thereof.
The first-stage upstream side heat shield ring 29 is divided into a plurality of portions in the circumferential direction, and a seal member (not shown) is interposed between them so as to prevent combustion gas and air from leaking.

On the upstream side of the inner peripheral portion of the first-stage upstream-side heat shield ring 29, an annular convex portion 43 that engages with a ring-shaped fitting groove 41 provided on the downstream end side of the partition plate outer ring 21 is provided. ing.
The first stage stationary blade 9 is firmly supported by the first stage blade ring 27 by supporting the downstream side of the partition plate outer ring 21 by the first stage upstream side heat shield ring 29 and supporting the upstream side by the mounting member 37. Yes.
Since the combustion gas introduced into the first stage stationary blade 9 is, for example, a high temperature of 1350 to 1500 ° C., the first stage stationary blade 9 (including other stationary blades and moving blades) has excellent high temperature strength, for example, nickel. It is made of a base heat-resistant alloy.

The first-stage upstream side heat shield ring 29 has a function of preventing high-temperature heat acting on the first-stage stationary blade 9 from being transmitted to the first-stage blade ring 27 not using a special heat-resistant material.
On the downstream side of the inner peripheral portion of the first-stage upstream-side heat shield ring 29, a first groove 45 formed in an annular shape for receiving a flange portion provided at an upstream end of the first-stage divided ring 33 described later, An annular second groove 47 that receives the upstream end of the impingement plate 39 is provided on the outer peripheral side of the first groove 45.
The inner peripheral surface 45a of the first groove 45 and the inner peripheral surface 29a of the first-stage upstream side heat shield ring 29 form a substantially smooth surface from the upstream side to the downstream side, in other words, an uneven surface. And constitutes a fitting part according to the present invention.

The first-stage downstream-side heat shield ring 31 is a substantially S-shaped annular part having an angular cross-sectional shape, and is divided into a plurality of first-stage downstream-side heat shield ring segments 32 in the circumferential direction. A seal member (not shown) is interposed between the first-stage downstream side heat shield ring segments 32 and sealed so that combustion gas and air do not leak.
The outer peripheral portion of the first-stage downstream-side heat shield ring 31 has a substantially rectangular cross-sectional shape, and the outer peripheral portion protrudes downstream.

The outer peripheral surface of the outer peripheral portion of the first stage downstream side heat shield ring 31 and the upstream side surface extending in the radial direction are formed so as to be substantially orthogonal to each other, and are formed in the lower part of the downstream side of the first stage blade ring 27, It is comprised so that it may fit in the cyclic | annular fitting groove | channel 49 which extends in the radial direction and the outer peripheral side forms the surface substantially orthogonal to it.
The outer peripheral surface of the first-stage downstream-side heat shield ring 31 and the outer peripheral side surface of the fitting groove 49 form a substantially smooth surface from the upstream side to the downstream side, in other words, an uneven surface, according to the present invention. The fitting part is comprised.

An upper surface of the downstream end portion of the first-stage downstream-side heat shield ring segment 32 is formed with a surface 52 that is substantially smooth from the upstream side to the downstream side, in other words, without unevenness, and is fitted according to the present invention. Part.
A concave portion 51 cut into a substantially rectangular shape is formed at the downstream end of the surface 52 and at a substantially central portion in the circumferential direction.
The inner peripheral surface of the recess 51 forms a substantially smooth surface from the upstream side to the downstream side, in other words, a surface having no unevenness, and constitutes a fitting portion according to the present invention.

At a substantially intermediate position in the radial direction of the first-stage downstream side heat shield ring segment 32, a portion 56 extending downstream is formed on the upstream side surface thereof.
A concave portion 53 that is cut into a substantially rectangular shape is formed at a substantially central portion in the circumferential direction of the portion 56.
The inner peripheral surface of the recess 53 forms a substantially smooth surface from the upstream side to the downstream side, in other words, a surface having no unevenness, and constitutes a fitting portion according to the present invention.
An engagement groove 55 that receives the downstream end of the impingement plate 39 is provided at the outer peripheral side position of the recess 53 on the upstream side surface of the first-stage downstream side heat shield ring segment 32. The engagement groove 55 is formed in an annular shape when the first-stage downstream-side heat shield ring segment 32 is combined to form the first-stage downstream-side heat shield ring 31.

On the upstream side of the inner peripheral portion of the first-stage downstream-side heat shield ring 31, there is a fitting groove 57 formed in an annular shape for receiving a flange portion provided at the downstream end of the first-stage divided ring 33 described later. Is provided.
The peripheral surface of the fitting groove 57 and the inner peripheral surface of the first-stage downstream-side heat shield ring 31 form a substantially smooth surface from the upstream side to the downstream side, in other words, an uneven surface. The fitting part by invention is comprised.
The first-stage downstream side heat shield ring 31 has a function of preventing high-temperature heat from the combustion gas from being transmitted to the first-stage blade ring 27 that does not use a special heat-resistant material.

The first-stage split ring 33 is an annular part that is excellent in high-temperature strength, for example, is formed of a nickel-based heat-resistant alloy, and is divided into a plurality of first-stage divided bodies 34 in the circumferential direction. A seal member (not shown) is interposed between the divided bodies 34 so as to prevent combustion gas and air from leaking.
An upstream flange portion 59 having a U-shaped cross section that opens to the upstream side is formed at the upstream end portion in the axial direction of the first stage split ring 33 so as to protrude to the outer peripheral side.
A downstream flange portion 61 having a U-shaped cross section that opens to the downstream side is formed at the downstream end portion in the axial direction of the first stage split ring 33 so as to protrude outward.
On the outer peripheral surface portion of the downstream flange 61, a convex portion 62 protruding outward and having a circumferential length substantially the same as the concave portion 53 of the first-stage downstream-side heat shield ring 31 is positioned so as to be fitted to the concave portion 53. Is provided.

The first-stage split ring 33 is formed so that the upstream flange portion 59 sandwiches the inner peripheral surface 29a of the first-stage upstream-side heat shield ring 29 and the inner peripheral surface 45a of the first groove 45, and the downstream flange portion. The first-stage upstream-side heat shield ring 29 and the first-stage downstream-side heat shield so that 61 sandwiches the inner peripheral surface 31a of the first-stage downstream-side heat shield ring 31 and the inner peripheral surface 57a of the fitting groove 57. Supported by the ring 31.
The first stage split ring 33 is arranged to face the outer peripheral surface of the first stage rotor blade 13, and the clearance between the first stage rotor blade 13 is set to a predetermined value, and the first stage rotor blade 13 is efficiently made. The rotational force of is obtained.

An air chamber 63 is formed by the first stage blade ring 27, the first stage upstream side heat shield ring 29, the first stage downstream side heat shield ring 31, and the first stage split ring 33. The air chamber 63 is configured to be supplied with cooling air by means not shown.
The impingement plate 39 is an annular member that is disposed in the air chamber 63 and has a cross-sectional shape formed in a recessed step shape.
The upstream end of the impingement plate 39 is fitted into the second groove 47 of the first stage upstream side heat shield ring 29, and the downstream end is fitted to the engagement groove 55 of the first stage downstream side heat shield ring 31. Thus, the impingement plate 39 is supported by the first stage upstream side heat shield ring 29 and the first stage downstream side heat shield ring 31.
A large number of ejection holes 65 are formed in the impingement plate 39.

The first stage fixing ring 35 is an annular part, and is divided into a plurality of fixing ring divided bodies 36 in the circumferential direction.
The circumferential end of the first stage fixing ring divided body 36 is cut in a step shape, and this stepped notch of the adjacent fixing ring divided body 36 is fitted to improve the sealing performance in the axial direction. ing.
The cross-sectional shape of the first stage fixing ring 35 is substantially rectangular. On the inner peripheral side of the first stage fixing ring 35, a protruding portion 35a having a rectangular cross section protruding upstream is provided. Further, a groove (annular recess) 35 b that is continuous in the circumferential direction is formed on the outer peripheral side of the first stage fixing ring 35 and on the upstream side.
On the first stage blade ring 27, an annular convex portion 50 that fits into the groove 35 b is formed on the outer peripheral side of the annular fitting groove 49 and on the downstream side.

The inner peripheral surface of the groove 35b is located at substantially the same position as the outer peripheral surface of the first stage downstream side heat shield ring 31.
The protruding portion 35a is configured to fit in a stepped manner with the downstream side surface of the first-stage downstream-side heat shield ring 31.
On the inner surface of the downstream end of the first stage fixing ring 35, a plurality of convex portions 67 projecting inward and having a substantially rectangular shape are provided at predetermined intervals.
The convex portion 67 has substantially the same length in the circumferential direction as the concave portion 51 of the first-stage downstream-side heat shield ring 31 and is provided at a position such that it fits into the convex portion 67.

The rectangular portion on the outer peripheral side of the first stage fixing ring 35 is configured to fit into a groove provided in the first stage blade ring 27 in substantially the same shape, and is fixed by a bolt 69.
The outer peripheral surface of the rectangular portion on the outer peripheral side of the first stage fixing ring 35 and the outer peripheral surface of the groove of the first stage blade ring 27 into which the first stage fixing ring 35 is fitted are substantially smooth from the upstream side to the downstream side, in other words, uneven. The surface which does not have is formed, and the fitting part by this invention is comprised.

  Between the upstream inner end of the first stage upstream side heat shield ring 29 and the partition plate outer ring 21, between the downstream inner end of the first stage upstream side heat shield ring 29 and the upstream flange part 59, the first Between the upstream inner end of the stage downstream side heat shield ring 31 and the downstream flange part 61 and between the first stage blade ring 27 and the first stage downstream side heat shield ring 31, it extends in the circumferential direction. A metal seal 71 is attached.

Next, the configuration of the second stage 7 will be described with reference to FIG.
FIG. 5 is a partially enlarged cross-sectional view showing an enlarged main part of the second stage blade ring structure 17.
The second stage blade ring structure 17 includes a second stage blade ring (turbine blade ring) 73, a second stage upstream side heat shield ring 75, and a second stage central heat shield ring (first heat shield ring) 77. A second-stage downstream side heat shield ring (second heat shield ring) 79, a second-stage divided ring (divided ring) 81, and a second-stage fixing ring (fixed ring) 83. .

The second stage blade ring 73 is formed by casting, for example, and includes a cylindrical space in which the second stage blade 19 can be accommodated, and constitutes a casing of the gas turbine 1.
The second stage upstream side heat shield ring 75 is an annular part having a substantially J-shaped cross section, and is fixed to the inside of the second stage blade ring 73 at the outer peripheral portion thereof.
The second-stage upstream side heat shield ring 75 is divided into a plurality of portions in the circumferential direction, and a seal member (not shown) is interposed between them so as to prevent combustion gas and air from leaking.
On the upstream side of the inner peripheral portion of the second-stage upstream-side heat shield ring 75, an annular convex portion 85 that engages with a ring-shaped fitting groove provided on the upstream end side of the partition plate outer ring 22 is provided. Yes.

The second stage central heat shield ring 77 is an annular part having a substantially rectangular cross-sectional shape and a downstream inner peripheral portion cut into a substantially rectangular shape. 73 is fixed to the inside.
The second-stage central heat shield ring 77 is divided into a plurality of portions in the circumferential direction, and a seal member (not shown) is interposed between them so as to prevent combustion gas and air from leaking.
On the downstream side of the inner peripheral portion of the second stage central heat shield ring 77, an annular convex portion 87 that engages with a ring-shaped fitting groove provided on the downstream end side of the partition plate outer ring 22 is provided. .
In the second stage stationary blade 15, the upstream side and the downstream side of the partition plate outer ring 22 are supported by the annular convex part 85 of the second stage upstream side heat shield ring 75 and the annular convex part 87 of the second stage central heat shield ring 77. Thus, the second stage blade ring 73 is firmly held.

The second stage upstream side heat shield ring 75 and the second stage central heat shield ring 77 transmit the high-temperature heat acting on the second stage stationary blade 15 to the second stage blade ring 73 not using a special heat resistant material. Has the function of preventing
The outer peripheral surface of the downstream end portion of the partition plate outer ring 22 extends substantially horizontally downstream, and this portion guides a flange portion provided at the upstream end portion of the second stage split ring 81 described later. It is configured as follows.
The outer ring 22 of the partition plate is integral with the second-stage central heat shield ring 77, and the outer peripheral surface of the downstream end of the outer ring 22 of the partition plate is substantially smooth from the upstream side to the downstream side. Since the surface which does not have is formed, the fitting part by this invention is comprised.

The second-stage downstream-side heat shield ring 79 is a substantially S-shaped annular part having an angular cross-sectional shape, and is divided into a plurality of parts in the circumferential direction, and a seal member (not shown) is interposed between them. And is sealed so that combustion gas and air do not leak.
The outer peripheral portion of the second-stage downstream-side heat shield ring 79 has a substantially rectangular cross-sectional shape, and the outer peripheral portion protrudes downstream.

The outer peripheral surface of the outer peripheral portion of the second stage downstream side heat shield ring 79 and the upstream side surface extending in the radial direction are formed so as to be substantially orthogonal to each other, and are formed at the lower part of the downstream side of the second stage blade ring 73, It is configured to fit in an annular fitting groove 89 that extends in the radial direction and forms a surface 89a that is substantially orthogonal to the outer peripheral side.
The outer peripheral surface of the second-stage downstream side heat shield ring 79 and the surface 89a of the fitting groove 89 form a substantially smooth surface from the upstream side to the downstream side, in other words, an uneven surface, according to the present invention. The fitting part is comprised.

On the upper part of the downstream end portion of the divided second-stage downstream-side heat shield ring 79, a surface 84 that is substantially smooth from the upstream side to the downstream side, in other words, has no unevenness, is formed. It constitutes a joint.
A concave portion 91 cut into a substantially rectangular shape is formed at the downstream end of the surface 84 and at a substantially central portion in the circumferential direction.
The inner peripheral surface of the recess 91 forms a substantially smooth surface from the upstream side toward the downstream side, in other words, a surface having no unevenness, and constitutes a fitting portion according to the present invention.

At a substantially intermediate position in the radial direction of the second stage downstream side heat shield ring 79, a portion 96 extending downstream is formed on the upstream side surface.
A concave portion 93 that is cut into a substantially rectangular shape is formed at a substantially central portion in the circumferential direction of the portion 96.
The inner peripheral surface of the recess 93 forms a substantially smooth surface from the upstream side to the downstream side, in other words, a surface having no unevenness, and constitutes a fitting portion according to the present invention.
On the outer peripheral surface portion of the downstream flange 99, a convex portion 94 that protrudes outward and has a circumferential length substantially equal to the concave portion 93 of the first-stage downstream-side heat shield ring 31 is located at a position where it fits into the concave portion 93. Is provided.

On the upstream side of the inner peripheral portion of the second-stage downstream side heat shield ring 79, there is an annular fitting groove 95 that receives a flange portion provided at the downstream end portion of the second-stage split ring 81 described later. Is provided.
The outer peripheral side surface of the fitting groove 95 and the inner peripheral surface 79a of the second-stage downstream side heat shield ring 79 form a substantially smooth surface from the upstream side to the downstream side, in other words, an uneven surface, The fitting part by this invention is comprised.
The second-stage downstream side heat shield ring 79 has a function of preventing high-temperature heat from the combustion gas from being transmitted to the second-stage blade ring 73 that does not use a special heat-resistant material.

The second-stage split ring 81 is an annular part that is excellent in high-temperature strength, for example, is formed of a nickel-base heat-resistant alloy, and is divided into a plurality of parts in the circumferential direction. A member is interposed and sealed so that combustion gas and air do not leak.
An upstream flange portion 97 that is bent to the upstream side next to the outer peripheral side is formed at the upstream end portion in the axial direction of the second stage split ring 81.
A downstream flange portion 99 having a U-shaped cross section that opens to the downstream side is formed at the downstream end portion in the axial direction of the second stage split ring 81 so as to protrude outward.

In the second stage split ring 81, the upstream flange portion 97 is sandwiched between the outer peripheral surface of the partition plate outer ring 22 and the inner peripheral surface of the second stage central heat shield ring 77, and the downstream flange portion 99 is downstream of the second stage. By sandwiching the inner peripheral surface 79 a of the side heat shield ring 79 and the outer peripheral side surface of the fitting groove 95, the side heat shield ring 79 is supported by the second stage central heat shield ring 77 and the second stage downstream heat shield ring 79.
The second stage split ring 81 is disposed to face the outer peripheral surface of the second stage rotor blade 19, and the clearance with the second stage rotor blade 19 is set to a predetermined value, so that the second stage rotor blade 19 can be efficiently used. The rotational force of is obtained.

  An air chamber 101 is formed by the second stage blade ring 73, the second stage central heat shield ring 77, the second stage downstream side heat shield ring 79, and the second stage split ring 81. The air chamber 101 is configured to be supplied with cooling air through the air supply path 103.

The second stage fixing ring 83 is an annular part, and is divided into a plurality of fixing ring divided bodies in the circumferential direction in the same manner as the first stage fixing ring 35.
The circumferential end of each fixing ring divided body is cut in a step shape, and the sealing performance in the axial direction is improved by fitting the stepped cutouts of adjacent fixing ring divided bodies.
The cross-sectional shape of the second stage fixing ring 83 is substantially rectangular. On the inner peripheral side of the second stage fixing ring 83, a protruding portion 83a having a rectangular cross section protruding upstream is provided. In addition, a groove (annular recess) 83 b that is continuous in the circumferential direction is formed on the outer peripheral side and the upstream side of the second stage fixing ring 83.
On the second stage blade ring 73, an annular convex portion 90 that fits into the groove 83b is formed on the outer peripheral side of the annular fitting groove 89 and on the downstream side.

The inner peripheral surface of the groove 83b is located at substantially the same position as the outer peripheral surface of the second-stage downstream-side heat shield ring 79.
The protrusion 83a is configured to fit in a stepped manner with the downstream side surface of the second-stage downstream-side heat shield ring 79.
On the inner peripheral surface of the downstream end portion of the second stage fixing ring 83, a plurality of convex portions 105 projecting toward the inner peripheral side and having a substantially rectangular shape are provided at predetermined intervals.
The convex portion 105 has substantially the same circumferential length as the concave portion 91 of the second-stage downstream-side heat shield ring 79, and is provided at a position where it fits into the convex portion 105.

The rectangular part on the outer peripheral side of the second stage fixing ring 83 is configured to fit into a groove provided in the second stage blade ring 73 in substantially the same shape, and is configured to be fixed by a bolt 107. .
The outer peripheral surface of the rectangular part on the outer peripheral side of the second stage fixing ring 83 and the outer peripheral surface of the groove of the second stage blade ring 73 into which the second stage fixing ring 83 is fitted are substantially smooth from the upstream side to the downstream side. The surface which does not have is formed, and the fitting part by this invention is comprised.
A seal member extending in the circumferential direction is mounted between the second stage blade ring 73 and the second stage downstream side heat shield ring 79.

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The assembly of the first stage blade ring structure 11 and the second stage blade ring structure 17 according to the present embodiment having the above-described configuration will be described.
First, assembly of the first stage blade ring structure 11 will be described.
Each divided body of the first-stage upstream side heat shield ring 29 is fitted into a fitting groove having a substantially reverse convex cross-section provided in the circumferential direction at a substantially central portion in the axial direction of the cast first-stage blade ring 27. Then, while inserting a seal member therebetween, the outer peripheral portions having substantially reverse convex shapes are inserted one by one from the circumferential direction, and the first stage upstream side heat shield ring 29 is incorporated.

Next, a metal seal 71 is attached to the inner end 43a of the annular convex portion 43 of the first stage upstream side heat shield ring 29 from the upstream side in the axial direction, and the fitting groove 41 of the partition plate outer ring 21 of the first stage stationary blade 9 is formed. The first stage stationary blade 9 is moved from the upstream side in the axial direction to the downstream side so as to cover the annular convex portion 43.
In this way, the fitting groove 41 of the partition plate outer ring 21 of the first stage stationary blade 9 is fitted to the annular convex portion 43, and the upstream side of the partition plate outer ring 21 is engaged with the mounting member 37, so that the first stage stationary blade 9 is engaged. Hold.

A metal seal 71 is attached to the upstream inner end portion 29b of the first stage upstream heat shield ring 29 from the downstream side in the axial direction.
An upstream flange portion 59 opened in a U-shape toward the upstream side of each first-stage divided body 34 of the first-stage divided ring 33 with a sealing member interposed therebetween is a first-stage upstream-side heat shield. The inner surface 29a of the ring 29 and the inner peripheral surface 45a of the first groove 45 are sandwiched and mounted so as to be guided by them from the downstream side in the axial direction to the upstream side. Thus, the first stage split ring 33 is assembled.
The upstream side surface of the upstream flange portion 59 abuts on the downstream side surface of the first stage upstream side heat shield ring 29, whereby the axial direction and radial position of each first stage divided body 34 are determined.
At the same time, the upstream end of the impingement plate 39 is inserted into the second groove 47 of the first stage upstream heat shield ring 29.

A metal seal 71 is attached from the downstream side in the axial direction to the downstream inner end portion of the fitting groove 49 of the first stage blade ring 27 and the downstream flange portion 61 of the first stage split ring 33.
Thereafter, each first-stage downstream-side heat shield ring segment 32 of the first-stage downstream-side heat shield ring 31 is assembled with a seal member interposed therebetween.
Each of the first-stage downstream-side heat shield ring segments 32 has an outer circumferential surface guided to an inner circumferential surface 49 a inside the fitting groove 49, and the inner circumferential surface 31 a of the downstream flange portion 61 of the first-stage divided ring 33. It is guided by the inner peripheral surface 61a and is mounted from the downstream side in the axial direction toward the upstream side.

At this time, the convex portion 62 provided on the outer periphery of the downstream flange portion 61 of the first-stage divided body 34 engages with the concave portion 53 of the first-stage downstream-side heat shield ring divided body 32, whereby the first-stage downstream-side shield. The positional relationship in the circumferential direction between the thermal ring segment 32 and the first stage segment 34 is defined in a predetermined manner.
Further, the downstream end portion of the impingement plate 39 is fitted into the engaging groove 55 of each first stage downstream side heat shield ring segment 32, and the impingement plate 39 is connected to the first stage upstream side heat shield ring 29 and the first stage. It is incorporated between the downstream side heat shield ring 31.

Next, each first stage fixing ring divided body 36 of the first stage fixing ring 35 is mounted.
Each first stage fixing ring divided body 36 is mounted from the downstream side in the axial direction toward the upstream side with the inner peripheral surface thereof guided by the surface 52 of the first stage downstream side heat shield ring 31.
At this time, the convex portion 67 provided on the inner periphery of the first stage fixed ring divided body 36 engages with the fitting groove 57 of the first stage downstream-side heat shield ring divided body 32, whereby the first stage downstream side. The positional relationship in the circumferential direction between the heat shield ring segment 32 and the first stage fixed ring segment 36 is defined in a predetermined manner.
At the same time, since the inner peripheral side portion of the first stage fixing ring 35 is combined with the outer peripheral side part of each first stage downstream side heat shield ring segment 32 in a stepped manner, the first stage downstream side heat shield ring segment is formed. 32 and by extension, the position of the first stage split ring 33 in the axial direction and the radial direction is defined as a predetermined position.
Further, by fitting the groove 35 b to the annular convex portion 50 of the first stage blade ring 27, the radial position of the first stage fixing ring 35 is defined at a predetermined position with respect to the first stage blade ring 27. The As a result, the first-stage downstream side heat shield ring 31 and the first-stage divided body 34 are defined to have predetermined positions in the radial direction with respect to the first-stage blade ring 27.

Since the first stage fixed ring divided body 36 is fixed to the first stage blade ring 27 by the bolt 69, the circumferential positional relationship with respect to the first stage blade ring 27 is attached to a predetermined position.
For this reason, each first stage downstream side heat shield ring divided body 32 is positioned in the circumferential direction by the first stage fixed ring divided body 36, so the first stage blades of the first stage downstream heat shield ring divided body 32 are arranged. The circumferential position with respect to the ring 27 can also be positioned at a predetermined position.
Accordingly, the circumferential position of the first stage divided body 34 with respect to the first stage blade ring 27 can also be positioned at a predetermined position.
At this time, the first-stage fixed ring divided body 36 simultaneously includes the first-stage downstream-side heat shield ring divided bodies 32 (first-stage downstream-side heat shield ring 31) and the first-stage divided bodies 34 (first-stage divided ring). 35) can be positioned at predetermined positions in the axial direction and the radial direction.

In this way, the first stage split ring 33, the first stage downstream heat shield ring 31 and the first stage fixing ring 35 are mounted from the downstream side to the upstream side in the axial direction, and the first stage fixing ring 35 is By fixing to the first stage blade ring 27 using the bolt 69, the first stage divided ring 33 and the first stage downstream side heat shield ring 31 are firmly fixed, and the first stage blade ring structure 11 is assembled. Therefore, the assembly of the first stage blade ring structure 11 is easy and can be easily performed between the supports.
Further, since the metal seal 71 extending in the circumferential direction is attached to each attachment position in the axial direction, the metal seal 71 does not move in contact with other members at the time of attachment. For this reason, since the surface of the metal seal 71 is not damaged, the deterioration of the sealing performance can be prevented.

Next, assembly of the second stage blade ring structure 17 will be described.
A second stage upstream side heat shield ring 75 and a fitting groove having a substantially reverse convex cross section provided in the circumferential direction in the axial direction upstream part and substantially central part of the cast second stage blade ring 73 respectively. Insert each of the divided parts of the second stage central heat shield ring 77 from the circumferential direction one by one from the circumferential direction while inserting a seal member between them, so that the second stage upstream heat shield Incorporate ring 75 and second stage central heat shield ring 77.

Next, the partition plate outer ring 22 of the second stage stationary blade 15 is fitted into the annular convex part 85 of the second stage upstream side heat shield ring 75 and the annular convex part 87 of the second stage central heat shield ring 77, and the second stage. The stage stationary blade 15 is held.
The upstream flange 97 is connected to the outer surface of the downstream end of the partition plate outer ring 22 and the second stage central heat shield ring 29 while inserting a seal member between the second stage divided bodies of the second stage divided ring 81. It is mounted from the downstream side in the axial direction toward the upstream side so as to be guided by the inner surface. In this way, the second stage split ring 81 is assembled.

A seal member extending in the circumferential direction is attached to the downstream inner end of the fitting groove 89 of the second stage blade ring 73 from the downstream side in the axial direction.
Thereafter, each second-stage downstream-side heat shield ring segment of the second-stage downstream-side heat shield ring 79 is assembled with a seal member interposed therebetween.
Each of the second-stage downstream-side heat shield ring segments is guided by an inner circumferential surface 89 a inside the fitting groove 89, and the inner circumferential surface 79 a is inside the downstream flange portion 99 of the second-stage divided ring 81. It is guided by the outer peripheral surface and is mounted from the downstream side in the axial direction toward the upstream side.
At this time, the convex portion 94 provided on the outer periphery of the downstream flange portion 99 of the second-stage divided ring 81 engages with the concave portion 93 of the second-stage downstream-side thermal insulation ring divided body, whereby the second-stage downstream-side heat shield. The positional relationship in the circumferential direction between the ring segment and the second stage segment is defined in a predetermined manner.

Next, the divided second stage fixing ring 83 is attached.
The inner peripheral surface of each second stage fixing ring 83 is guided from the surface 84 of the second stage downstream side heat shield ring 83 and mounted from the downstream side in the axial direction toward the upstream side.
At this time, the convex portion 105 provided on the inner periphery of the second stage fixing ring 83 engages with the fitting groove 95 of the second stage downstream side heat shield ring 79, whereby the second stage downstream side heat shield ring 79. And a circumferential positional relationship between the second stage split ring 81 and the second stage split ring 81 are prescribed.
At the same time, since the inner periphery of the second stage fixing ring 83 is combined with the outer periphery of the first stage downstream side heat shield ring 79 in a stepped manner, the second stage downstream side heat shield ring 79, and thus the second stage division. The positions of the ring 81 in the axial direction and the radial direction are defined as predetermined positions.
Further, the groove 83 b is fitted into the annular convex portion 90 of the second stage blade ring 73, so that the second stage fixing ring 83 has a predetermined radial position with respect to the second stage blade ring 73. The Thereby, the radial position of the second stage downstream side heat shield ring 79 and the second stage divided body 81 with respect to the second stage blade ring 73 is defined at a predetermined position.

Since the second stage fixing ring 83 is fixed to the second stage blade ring 73 by the bolt 107, the circumferential positional relationship with respect to the second stage blade ring 73 is attached to a predetermined position.
Therefore, the second stage downstream side heat shield ring 79 is positioned in the circumferential direction by the second stage fixing ring 83, and therefore the circumferential position of the second stage downstream side heat shield ring 79 relative to the second stage blade ring 73 is also determined. It can be positioned at a predetermined position.
Accordingly, the circumferential position of the second stage split ring 81 with respect to the second stage blade ring 73 can also be positioned at a predetermined position.
At this time, the second stage fixing ring 83 can simultaneously position the second stage downstream side heat shield ring 79 and the second stage split ring 81 in the axial direction and the radial direction at predetermined positions.

Thus, the second stage split ring 81, the second stage downstream heat shield ring 79, and the second stage fixing ring 83 are mounted from the downstream side to the upstream side in the axial direction, and the second stage fixing ring 83 is mounted. By fixing to the second stage blade ring 73 using the bolt 107, the second stage divided ring 81 and the second stage downstream side heat shield ring 79 are firmly fixed, and the second stage blade ring structure 17 is assembled. Therefore, the assembly of the second stage blade ring structure 17 is easy and can be easily performed between the supports.
In addition, the circumferentially extending seal member interposed between the second stage blade ring 73 and the second stage downstream side heat shield ring 79 is mounted in the axial direction at the mounting position. It does not move in contact with the members. For this reason, since the surface of the sealing member is not damaged, it is possible to prevent deterioration of the sealing performance.

The first stage blade ring structure 11 and the second stage blade ring structure 17 in the present embodiment described above are not limited to this, and various modifications are made without departing from the spirit of the present invention. May be.
For example, in the present embodiment, the fitting surface is formed so as to be substantially horizontal in cross section, but may be inclined inward or outward toward the downstream side.

It is a longitudinal section showing a part of gas turbine to which one embodiment of the present invention is applied. It is a fragmentary longitudinal cross-section which shows the 1st step blade ring structure concerning one Embodiment of this invention. FIG. 3 is an X view of FIG. 2 shown in an enlarged manner. FIG. 3 is an X view of FIG. 2. It is a fragmentary longitudinal cross-section which shows the 2nd stage blade ring structure concerning one Embodiment of this invention.

Explanation of symbols

11 First-stage blade ring structure 13 First-stage blade 17 Second-stage blade ring structure 19 Second-stage blade 29 First-stage upstream heat shield ring 31 First-stage downstream heat shield ring 33 First-stage split ring 35 First stage fixing ring 35b Groove 50 Annular convex part 51 Concave part 53 Concave part 62 Convex part 67 Convex part 77 Second stage central heat shield ring 79 Second stage downstream side heat shield ring 81 Second stage split ring 83 Second stage fixed part Ring 83b Groove 90 Annular convex part 91 Concave part 93 Concave part 94 Convex part 105 Convex part

Claims (5)

A first heat shield ring divided into a plurality in the circumferential direction and supported by the turbine blade ring;
A second heat shield ring that is arranged at an interval downstream from the first heat shield ring in the axial direction of the turbine blade ring and is divided into a plurality of portions in the circumferential direction and supported by the turbine blade ring;
A split ring that is divided into a plurality in the circumferential direction of the turbine blade ring and supported by the first heat shield ring and the second heat shield ring to maintain a clearance with the rotor blade;
A fixed ring that is divided into a plurality in the circumferential direction, presses the second heat shield ring to the upstream side in the axial direction, and is fixed to the turbine blade ring,
At least the turbine blade ring excluding the fitting portion of the first heat shield ring to the turbine blade ring, the first heat shield ring, the split ring, the second heat shield ring, and the fixed ring. A turbine blade ring structure characterized in that the insertion side of the fitting portion is opened toward the downstream side in the axial direction.   The fitting portion between the turbine blade ring and the fixed ring includes an annular convex portion in which one circumferential portion projects toward the other and an annular concave portion into which the annular convex portion is fitted. The turbine blade ring structure according to claim 1, wherein the turbine blade ring structure is provided.   At the downstream end of the fitting portion between the fixing ring and the second heat shield ring, a convex portion in which one of the circumferential directions protrudes toward the other and the convex portion is fitted to the other. 3. The turbine blade ring structure according to claim 1, further comprising: a concave portion that is configured to be recessed.   At the upstream end of the fitting portion between the split ring and the second heat shield ring, a convex portion in which one of the circumferential directions protrudes toward the other and this convex portion is fitted into the other. The turbine blade ring structure according to any one of claims 1 to 3, further comprising a concave portion that is configured to be provided.   A first heat shield ring that is divided into a plurality of parts in the circumferential direction and supported by the turbine blade ring, and is arranged at an interval from the first heat shield ring to the downstream side in the axial direction of the turbine blade ring; A second heat shield ring divided into a plurality of directions and supported by the turbine blade ring; and a plurality of first heat shield rings and a second heat shield ring divided in the circumferential direction of the turbine blade ring And is divided into a plurality of parts in the circumferential direction, each pressing the second heat shield ring to the upstream side in the axial direction and being fixed to the turbine blade ring. A fixed ring, and the turbine blade ring as an assembly member, the first heat shield ring, the split ring, the second heat shield ring, and at least the first heat shield ring of the fixed ring. The inserted side of the mutual fitting part except the fitting part to the turbine blade ring is in the axial direction. The turbine blade ring structure is opened toward the downstream side of the turbine blade ring, and after the first heat shield ring is attached to the turbine blade ring, the split ring, the second heat shield ring, and When the fixing ring is assembled along the mutual fitting surface in the axial direction and the fixing ring is fixed to the turbine blade ring and assembled, and the fitting portion has a seal member extending in the circumferential direction. A method for assembling a turbine blade ring structure, wherein the next assembly member is attached after the seal member is attached to the previous assembly member from the axial direction.

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