TURBINE

Abstract

To provide a turbine that is capable of deforming (tilting) of a support portion (more specifically, a circular-truncated cone portion). A turbine that is provided with a vertically divided casing that is divided into two portions in a longitudinal direction and a support portion that supports a stator-blade ring disposed in the casing, wherein the support portion is provided with a flange portion that is secured between a joining surface of one portion of the casing and a joining surface of the other portion of the casing, being sandwiched therebetween, and a circular-truncated cone portion that connects the flange portion and a stator-blade holding ring, and wherein a thick plate portion having a greater plate thickness than the plate thickness of the flange portion and the stator-blade holding ring is provided between the flange portion located at a lower-half portion and the stator-blade holding ring.

Description

TECHNICAL FIELD

The present invention relates a turbine, and it relates in particular to a turbine that obtains a rotational force using a high-temperature working fluid.

BACKGROUND ART

Known turbines that obtain a rotational force using a high-temperature working fluid include, for example, the disclosure in Patent Literature 1.

CITATION LIST

Patent Literature

• {PTL 1} Japanese Unexamined Patent Application, Publication No. 2001-264477.

SUMMARY OF INVENTION

Technical Problem

Turbines that obtain a rotational force using a high-temperature working fluid include those provided with a vertically divided (pot-shaped) casing that is divided into two portions in a longitudinal direction (front-back direction) and a support portion that supports a stator-blade holding ring disposed inside the casing.

The conventional support portion, however, is formed so that a mortar-shaped circular-truncated cone portion that connects a flange portion and the stator-blade holding ring becomes vertically asymmetrical, that is, so that its length (width) becomes gradually longer from a top portion (upper portion) side to a bottom portion (lower portion) side.

Because of this, the surface area (pressure-receiving area) of a lower-half portion becomes larger than the surface area (pressure-receiving area) of an upper-half portion and, due to a difference (pressure difference) between pressure that acts on a high-pressure side surface of the support portion (more specifically, the circular-truncated cone portion) and pressure that acts on a low-pressure side surface of the support portion (more specifically, the circular-truncated cone portion), the support portion (more specifically, the circular-truncated cone portion) may become deformed (tilted) so as to bow down.

In addition, a high-temperature working fluid (for example, combustion gas or steam) that passes through the interior of the stator-blade holding ring causes an asymmetrical differential thermal expansion in the support portion (more specifically, the circular-truncated cone portion), and this may cause the support portion (more specifically, the circular-truncated cone portion) to become deformed (inclined) so as to bow down.

The present invention has been conceived in light of the above-described circumstances, and an object thereof is to provide a turbine that is capable of preventing deforming (tilting) of a support portion (more specifically, the circular-truncated cone portion) due to a pressure difference or differential thermal expansion.

Solution to Problem

In order to solve the above-described problems, the present invention employs the following solutions.

A turbine according to a first aspect of the present invention is a turbine that is provided with a vertically divided casing that is divided into two portions in a longitudinal direction; and a support portion that supports a stator-blade holding ring disposed in the casing, wherein, the support portion is provided with a flange portion that is secured between a joining surface of one portion of the casing and a joining surface of the other portion of the casing, being sandwiched therebetween, and a circular-truncated cone portion that connects the flange portion and the stator-blade holding ring, and wherein a thick plate portion having a greater plate thickness than the plate thickness of the flange portion and the stator-blade holding ring is provided between the flange portion located at a lower-half portion and the stator-blade holding ring.

With the turbine according to the first aspect of the present invention, because the rigidity of the support portion as a whole is increased (enhanced) by the thick plate portion provided (formed) in the support portion, it is possible to prevent deforming (tilting) of the support portion (more specifically, the circular-truncated cone portion) caused by a difference (pressure difference) between pressure that acts on a high-pressure side surface of the support portion (more specifically, the circular-truncated cone portion) and pressure that acts on a low-pressure side surface of the support portion (more specifically the circular-truncated cone portion).

In addition, with the thick plate potion provided (formed) in the support portion, it is possible to prevent asymmetrical differential thermal expansion of the support portion (more specifically, the circular-truncated cone portion) caused by having a high-temperature working fluid (for example, combustion gas or steam) pass through the inside of the stator-blade holding ring, and it is also possible to prevent deforming (tilting) of the support portion (more specifically, the circular-truncated cone portion) caused by this asymmetrical differential thermal expansion.

Furthermore, because deforming of the support portion can be prevented, a tip clearance between tips (distal ends) of the turbine blades and an inner circumferential surface of the stator-blade holding ring can be held constant, thereby making it possible to reduce leakage (tip leakage) from the tips of the turbine blades; and thus, turbine efficiency (performance) can be enhanced, and contact between the tips of the turbine blades and the inner circumferential surface of the stator-blade holding ring can also be prevented, making it possible to prevent damage to and breakage of the turbine blades and turbine nozzles. Accordingly, the reliability of the turbine can be enhanced.

A turbine according to a second aspect of the present invention is a turbine that is provided with a vertically divided casing that is divided into two portions in a longitudinal direction; and a support portion that supports a stator-blade holding ring disposed in the casing, wherein, the support portion is provided with a flange portion that is secured between a joining surface of one portion of the casing and a joining surface of the other portion of the casing, being sandwiched therebetween, and a circular-truncated cone portion that connects the flange portion and the stator-blade holding ring, and wherein the flange portion is formed so that the plate thickness thereof gradually increases from a radially outer side toward a radially inner side thereof, and so that the joining surfaces of the casing coincide with the joining surfaces of the flange portion.

With the turbine according to the second aspect of the present invention, the flange portion provided (formed) in the support portion increases (enhances) the rigidity of the support portion as a whole; therefore, it is possible to prevent deforming (tilting) of the support portion (more specifically, the circular-truncated cone portion) caused by a difference (pressure difference) between pressure that acts on a high-pressure side surface of the support portion (more specifically, the circular-truncated coned portion) and pressure that acts on a low-pressure side surface of the support portion (more specifically, the circular-truncated cone portion).

In addition, with the flange portion provided (formed) in the support portion, it is possible to prevent asymmetrical differential thermal expansion of the support portion (more specifically, the circular-truncated cone portion) caused by having a high-temperature working fluid (for example, combustion gas or steam) pass through the inside of the stator-blade holding ring, and it is also possible to prevent deforming (tilting) of the support portion (more specifically, the circular-truncated cone portion) caused by this asymmetrical differential thermal expansion.

Furthermore, because deforming of the support portion can be prevented, a tip clearance between the tips (distal ends) of the turbine blades and the inner circumferential surface of the stator-blade holding ring can be held constant, thereby making it possible to reduce leakage (tip leakage) from the tips of the turbine blades; and thus, the turbine efficiency (performance) can be enhanced, and contact between the tips of the turbine blades and the inner circumferential surface of the stator-blade holding ring can also be prevented, making it possible to prevent damage to and breakage of the turbine blades and turbine nozzles. Accordingly, the reliability of the turbine can be enhanced.

In addition, in the turbine according to the second aspect of the present invention, the joining surface of the front casing and the joining surface of the flange portion are individually formed as tapered surfaces (formed like a circular truncated cone); therefore, when assembling the casing, coupling alignment (centering) between the casing and the support portion can be easily performed, thereby making it possible to shorten the processing time required for assembling the casing.

A turbine according a third aspect of the present invention is a turbine that is provided with a vertically divided casing that is divided into two portions in a longitudinal direction; and a support portion that supports a stator-blade holding ring disposed in the casing, wherein, the support portion is provided with a flange portion that is secured between a joining surface of one portion of the casing and a joining surface of the other portion of the casing, being sandwiched therebetween, and a circular-truncated cone portion that connects the flange portion and the stator-blade holding ring, and wherein a ring fabricated using a high thermal expansion material as a constituent is provided between an outer circumferential surface of the circular-truncated cone portion and an inner circumferential surface of the front casing.

With the turbine according to the third aspect of the present invention, due to a high-temperature working fluid (for example, combustion gas or steam) passing through the inside of the stator-blade holding ring, the ring expands at a greater thermal expansion rate than the casing and the support portion, thereby causing an outer circumferential surface of the circular-truncated cone portion and an inner circumferential surface (circumferential surface on radially inner side) of the ring to come into close contact with each other, which also causes an inner circumferential surface of the casing and an outer circumferential surface (circumferential surface on radially outer side) of the ring to come into close contact with each other; therefore, a space formed between the outer circumferential surface of the circular-truncated cone portion and the inner circumferential surface of the casing is completely filled with the ring, without any gap.

Accordingly, despite the tendency of the support portion (more specifically, the circular-truncated cone portion) to deform (tilt) due to a pressure difference or differential thermal expansion during turbine operation, deforming (tilting) of the support portion (more specifically, the circular-truncated cone portion) is prevented by the ring disposed (interposed) between the outer circumferential surface of the circular-truncated cone portion and the inner circumferential surface of the casing.

Consequently, a tip clearance between the tips (distal ends) of the turbine blades and the inner circumferential surface of the stator-blade holding ring can be held constant, thereby making it possible to reduce the leakage (tip leakage) from the tips of the turbine blades; and thus, the turbine efficiency (performance) can be enhanced, and contact between the tips of the turbine blades and the inner circumferential surface of the stator-blade holding ring can also be prevented, making it possible to prevent damage to and breakage of the turbine blades and turbine nozzles. Accordingly, the reliability of the turbine can be enhanced.

A turbine according to a fourth aspect of the present invention is a turbine that is provided with a vertically divided casing that is divided into two portions in a longitudinal direction; and a support portion that supports a stator-blade holding ring disposed in the casing, wherein, the support portion is provided with a flange portion that is secured between a joining surface of one portion of the casing and a joining surface of the other portion of the casing, being sandwiched therebetween, and a circular-truncated cone portion that connects the flange portion and the stator-blade holding ring, and wherein the circular-truncated cone portion is formed so as to have a fixed length in a circumferential direction.

With the turbine according to the fourth aspect of the present invention, because the circular-truncated cone portion is provided (formed) so as to have a fixed length (width) over the circumferential direction, it is possible to prevent asymmetrical differential thermal expansion of the support portion (more specifically, the circular-truncated cone portion), as well as deforming (tilting) of the support portion (more specifically, the circular-truncated cone portion) that are caused by a difference (pressure difference) between pressure that acts on a high-pressure side surface of the support portion (more specifically, the circular-truncated coned portion) and pressure that acts on a low-pressure side surface of the support portion (more specifically, the circular-truncated cone portion) and by having a high-temperature working fluid (for example, combustion gas or steam) pass through the inside of the stator-blade holding ring.

Furthermore, because deforming of the support portion can be prevented, a tip clearance between tips (distal ends) of the turbine blades and the inner circumferential surface of the stator-blade holding ring can be held constant, thereby making it possible to reduce leakage (tip leakage) from the tips of the turbine blades; and thus, the turbine efficiency (performance) can be enhanced, and contact between the tips of the turbine blades and the inner circumferential surface of the stator-blade holding ring can also be prevented, making it possible to prevent damage to and breakage of the turbine blades and the turbine nozzles. Accordingly, the reliability of the turbine can be enhanced.

In the above-described turbine, it is more preferable that the plate thickness at a lower-half portion of the circular-truncated portion be greater than the plate thickness at an upper-half portion of the circular-truncated portion.

With such a turbine, the rigidity of the support portion can be further enhanced; the tip clearance between the tips (distal ends) of the turbine blades and the inner circumferential surface of the stator-blade holding ring can be held constant, thereby making it possible to further reduce a leakage (tip leakage) from the tips of the turbine blades; and thus, the turbine efficiency (performance) can be further enhanced, and contact between the tips of the turbine blades and the inner circumferential surface of the stator-blade holding ring can also be prevented, making it possible to prevent damage to and breakage of the turbine blades and turbine nozzles. Accordingly, the reliability of the turbine can be further enhanced.

Advantageous Effects of Invention

According to the present invention, an advantage is afforded in that it is possible to prevent deforming (tilting) of a support portion (more specifically, a circular-truncated cone portion) due to a pressure difference or a differential thermal expansion.

BRIEF DESCRIPTION OF DRAWINGS

FIG. 1 is a lateral sectional view of a turbine according to a first embodiment of the present invention.

FIG. 2 is a perspective sectional view of relevant portions of the turbine shown in FIG. 1.

FIG. 3 is a longitudinal sectional view of relevant portions of a support portion shown in FIG. 1.

FIG. 4 is an enlarged view of relevant portions of a turbine according to a second embodiment of the present invention.

FIG. 5 is an enlarged view of relevant portions of a turbine according to a third embodiment of the present invention.

FIG. 6 is an enlarged view of relevant portions of a turbine according to a fourth embodiment of the present invention.

FIG. 7 is a perspective sectional view of relevant portions of a turbine according to a fifth embodiment of the present invention.

DESCRIPTION OF EMBODIMENTS

A first embodiment of a turbine according to the present invention will be described below with reference to FIGS. 1 to 3.

FIG. 1 shows a lateral sectional view of a turbine according to the first embodiment of the present invention; FIG. 2 is a perspective sectional view of relevant portions of the turbine shown in FIG. 1; and FIG. 3 is a longitudinal sectional view of relevant portions of a support portion shown in FIG. 1.

A turbine 1 obtains a rotational force using, for example, high-temperature steam from a boiler (not shown); using this rotational force, drives a generator connected via a rotation shaft; and, as shown in FIG. 1, is configured to include a turbine rotor 2 and a casing 3 as main components.

Individual end portions of the turbine rotor 2 are supported on support bases (frame) via bearings (journal bearings) in a rotatable manner, and a plurality of turbine blades (rotor blades) are attached to individual outer circumferential portions of the turbine rotor 2 along the circumferential direction.

The casing 3 is a vertically divided casing that is divided into two portions in a front-back direction (left-right direction in FIG. 1) and is provided with a front casing 3a located on the right side in FIG. 1 and a rear casing 3b located on the left side in FIG. 1. In addition, flange portions 9a of a support portion 9 that supports a stator-blade holding ring 8 are configured so as to be sandwiched between the front casing 3a and the rear casing 3b.

The stator-blade holding ring 8 is disposed so as to surround the turbine rotor 2 and the turbine blades on the radially outer side, and, at its inner circumferential portion, a plurality of turbine nozzles (stator blades) are attached along the circumferential direction.

As shown in FIGS. 1 and 2, the support portion 9 includes the flange portions 9a, circular-truncated cone portions 9b, and thick plate portions 9c.

The flange portions 9a are plate-like members that are ring-like (doughnut-like) in plan view, having a fixed thickness and a fixed length (width) over the circumferential direction, and are secured, via a plurality of bolts (fastening members), between a joining surface of the front casing 3a (see FIG. 1) and a joining surface of the rear casing 3b (see FIG. 1) in an attachable/detachable manner.

The circular-truncated cone portions 9b are mortar-like members that have a fixed thickness and a fixed length (width) over the circumferential direction; that protrude backward (from a front casing 3a side toward a rear casing 3b side); that connect the flange portions 9a and the stator-blade holding ring 8 at upper-half portions thereof; and that connect the thick plate portions 9c and the stator-blade holding ring 8 at lower-half portions thereof.

As shown in FIG. 3, the thick plate portions 9c are plate-like members that are crescent-like in plan view and that are formed so that the plate thickness thereof is greater than the plate thickness of the flange portions 9a and the circular-truncated cone portions 9b.

Note that the “plate thickness” of the thick plate portions 9c refers to a thickness in a direction parallel to a direction in which a turbine axis (axis in the longitudinal direction: rotational axis) of the turbine 1 (see FIG. 1) extends, which is indicated by a reference sign C in FIG. 2; in other words, it refers to a thickness in the left-right direction in FIG. 1.

With the turbine 1 according to this embodiment, the thick plate portions 9c provided (formed) in the support portion 9 increase (enhance) the rigidity of the support portion 9 as a whole; therefore, it is possible to prevent deforming (tilting) of the support portion 9 (more specifically, the circular-truncated cone portions 9b) caused by a difference (pressure difference) between pressure that acts on a high-pressure side (right side in FIG. 1) surface of the support portion 9 (more specifically, the circular-truncated coned portions 9b) and pressure that acts on a low-pressure side (left side in FIG. 1) surface of the support portion 9 (more specifically, the circular-truncated cone portions 9b).

In addition, with the thick plate portions 9c provided (formed) in the support portion 9, it is possible to prevent an asymmetrical differential thermal expansion of the support portion 9 (more specifically, the circular-truncated cone portions 9b) caused by having a high-temperature working fluid (for example, combustion gas or steam) pass through the inside of the stator-blade holding ring 8, as well as deforming (tilting) of the support portion 9 (more specifically, the circular-truncated cone portions 9b) caused by this asymmetrical differential thermal expansion.

Furthermore, because deforming of the support portion 9 can be prevented, a tip clearance between tips (distal ends) of the turbine blades and an inner circumferential surface of the stator-blade holding ring 8 can be held constant, thereby making it possible to reduce leakage (tip leakage) from the tips of the turbine blades; and thus, turbine efficiency (performance) can be enhanced and contact between the tips of the turbine blades and the inner circumferential surface of the stator-blade holding ring 8 can also be prevented, making it possible to prevent damage to and breakage of the turbine blades and the turbine nozzles. Accordingly, the reliability of the turbine 1 can be enhanced.

A second embodiment of the turbine according to the present invention will be described with reference to FIG. 4.

FIG. 4 is an enlarged view of relevant portions of a turbine according to this embodiment.

A turbine 21 according to this embodiment differs from the above-described first embodiment in that a support portion 22 is provided instead of the support portion 9. Because other constituent components are the same as those in the above-described first embodiment, descriptions of those constituent components will be omitted.

The support portion 22 according to this embodiment is provided with flange portions 22a and circular-truncated cone portions 22b.

The flange portions 22a are plate-like members that are ring-like (doughnut-like) in plan view, having a fixed thickness and a fixed length (width) over the circumferential direction, and are secured, via a plurality of bolts (fastening members), between the joining surface of the front casing 3a and the joining surface of the rear casing 3b in an attachable/detachable manner.

The circular-truncated cone portions 22b are mortar-like members that have a fixed thickness over the circumferential direction; that protrude backward (from the front casing 3a side toward the rear casing 3b side); and that connect the flange portions 22a and the stator-blade holding ring 8 in the circumferential direction.

In addition, outer circumferential surfaces (circumferential surfaces at the radially outer side) 23 of the circular-truncated cone portions 22b are provided (formed) so as to be located in the vicinity of inner circumferential surfaces 24 of the front casing 3a and the rear casing 3b, that is, so as to be located as close as possible to the inner circumferential surfaces 24 of the front casing 3a and the rear casing 3b.

Thus, just a slight deforming (tilting) of the support portion 22 (more specifically, the circular-truncated cone portions 22b) caused by a pressure difference or differential thermal expansion brings the outer circumferential surfaces 23 of the circular-truncated cone portions 22b into contact with the inner circumferential surfaces 24 of the front casing 3a, thereby preventing any further deforming (tilting) of the support portion 22 (more specifically, the circular-truncated cone portions 22b).

With the turbine 21 according to this embodiment, deforming (tilting) of the support portion 22 (more specifically, the circular-truncated cone portions 22b) caused by a pressure difference or differential thermal expansion can be suppressed to the minimum (significantly reduced); therefore, the tip clearance between the tips (distal ends) of the turbine blades and the stator-blade holding ring 8 can be held substantially constant, thereby making it possible to reduce the leakage (tip leakage) from the tips of the turbine blades; and thus, the turbine efficiency (performance) can be enhanced and contact between the tips of the turbine blades and the inner circumferential surface of the stator-blade holding ring 8 can also be prevented, making it possible to prevent damage to and breakage of the turbine blades and the turbine nozzles. Accordingly, the reliability of the turbine 21 can be enhanced.

A third embodiment of the turbine according to the present invention will be described with reference to FIG. 5.

FIG. 5 is an enlarged view of relevant portions of a turbine according to this embodiment.

A turbine 31 according to this embodiment differs from the above-described first embodiment in that a support portion 32 is provided instead of the support portion 9. Because other constituent components are the same as those in the above-described first embodiment, descriptions of those constituent components will be omitted.

The support portion 32 according to this embodiment is provided with flange portions 32a and circular-truncated cone portions 32b.

The flange portions 32a are plate-like members that are ring-like (doughnut-like) in plan view and that are formed so as to gradually increase in thickness from a radially outer side toward a radially inner side as well as to have a fixed length (width) in the circumferential direction, and are secured, via a plurality of bolts (fastening members), between the joining surface of the front casing 3a and the joining surface of the rear casing 3b in an attachable/detachable manner. Note that, as shown in FIG. 5, the joining surfaces 33 of the front casing 3a in this embodiment are provided (formed) so as to coincide with (come in contact with) joining surfaces 34 of the flange portions 32a.

The circular-truncated cone portions 32b are mortar-like members that have a fixed thickness over the circumferential direction; that protrude backward (from the front casing 3a side toward the rear casing 3b side); and that connect the flange portions 32a and the stator-blade holding ring 8.

With the turbine 31 according to this embodiment, the flange portions 32a provided (formed) in the support portion 32 increase (enhance) the rigidity of the support portion 32 as a whole; therefore, it is possible to prevent deforming (tilting) of the support portion 32 (more specifically, the circular-truncated cone portions 32b) caused by a difference (pressure difference) between pressure that acts on a high-pressure side (right side in FIG. 5) surface of the support portion 32 (more specifically, the circular-truncated coned portions 32b) and pressure that acts on a low-pressure side (left side in FIG. 5) surface of the support portion 32 (more specifically, the circular-truncated cone portions 32b).

In addition, with the flange portions 32a provided (formed) in the support portion 32, it is possible to prevent asymmetrical differential thermal expansion of the support portion 32 (more specifically, the circular-truncated cone portions 32b) caused by having a high-temperature working fluid (for example, combustion gas or steam) pass through the inside of the stator-blade holding ring 8, as well as deforming (tilting) of the support portion 32 (more specifically, the circular-truncated cone portions 32b) caused by this asymmetrical differential thermal expansion.

Furthermore, because deforming of the support portion 32 can be prevented, the tip clearance between the tips (distal ends) of the turbine blades and the inner circumferential surface of the stator-blade holding ring 8 can be held constant, thereby making it possible to reduce leakage (tip leakage) from the tips of the turbine blades; and thus, the turbine efficiency (performance) can be enhanced, and contact between the tips of the turbine blades and the inner circumferential surface of the stator-blade holding ring 8 can also be prevented, making it possible to prevent damage to and breakage of the turbine blades and the turbine nozzles. Accordingly, the reliability of the turbine 31 can be enhanced.

In addition, in the turbine 31 according to this embodiment, the joining surfaces 33 of the front casing 3a and the joining surfaces 34 of the flange portions 32a are individually formed as tapered surfaces (formed like a circular truncated cone); therefore, when assembling the casing 3, coupling alignment (centering) between the front casing 3a and the support portion 32 can be easily performed, thereby making it possible to shorten the processing time required for assembling the casing 3.

A fourth embodiment of the turbine according to the present invention will be described with reference to FIG. 6.

FIG. 6 is an enlarged view of relevant portions of a turbine according to this embodiment.

A turbine 41 according to this embodiment differs from the above-described second embodiment in that a ring 42 is provided between the outer circumferential surfaces 23 of the circular-truncated cone portions 22b and the inner circumferential surfaces 24 of the front casing 3a. Because other constituent components are the same as those in the above-described second embodiment, descriptions of those constituent components will be omitted.

The ring 42 is a thin plate-like member that is ring-like (doughnut-like) in plan view, having a fixed thickness and a fixed length (width) over the circumferential direction, and is fabricated using a high-thermal-expansion material (for example, SUS304) as a constituent. Note that the casing 3 and the support portion 22 are fabricated using, as constituents, metal materials (for example, alloys containing 2Cr) having lower thermal expansion rates than the ring 42.

In other words, due to a high-temperature working fluid (for example, combustion gas or steam) passing through the inside of the stator-blade holding ring 8, the ring 42 expands at a greater thermal expansion rate than the casing 3 and the support portion 22, thereby causing the outer circumferential surfaces 23 of the circular-truncated cone portions 22b and an inner circumferential surface (circumferential surface on radially inner side) of the ring 42 to come into close contact with each other, which also causes the inner circumferential surfaces 24 of the front casing 3a and an outer circumferential surface (circumferential surface on radially outer side) of the ring 42 to come into close contact with each other; therefore, a space formed between the outer circumferential surfaces 23 of the circular-truncated cone portions 22b and the inner circumferential surfaces 24 of the front casing 3a is completely filled with the ring 42, without any gap.

Accordingly, despite the tendency of the support portion 22 (more specifically, the circular-truncated cone portions 22b) to deform (tilt) due to a pressure difference or differential thermal expansion during turbine operation, deforming (tilting) of the support portion 22 (more specifically, the circular-truncated cone portions 22b) is prevented by the ring 42 disposed (interposed) between the outer circumferential surfaces 23 of the circular-truncated cone portions 22b and the inner circumferential surfaces 24 of the front casing 3a.

With the turbine 42 according to this embodiment, because deforming (tilting) of the support portion 22 (more specifically, the circular-truncated cone portions 22b) due to a pressure difference or differential thermal expansion can be prevented, the tip clearance between the tips (distal ends) of the turbine blades and the inner circumferential surface of the stator-blade holding ring 8 can be held constant, thereby making it possible to reduce leakage (tip leakage) from the tips of the turbine blades; and thus, the turbine efficiency (performance) can be enhanced, and contact between the tips of the turbine blades and the inner circumferential surface of the stator-blade holding ring 8 can also be prevented, making it possible to prevent damage to and breakage of the turbine blades and the turbine nozzles. Accordingly, the reliability of the turbine 41 can be enhanced.

A fifth embodiment of the turbine according to the present invention will be described with reference to FIG. 7.

FIG. 7 is a perspective sectional view of relevant portions of a turbine according to this embodiment.

A turbine 51 according to this embodiment differs from the above-described first embodiment in that a support portion 52 is provided instead of the support portion 9. Because other constituent components are the same as those in the above-described first embodiment, descriptions of those constituent components will be omitted.

The support portion 52 according to this embodiment is provided with flange portions 52a and circular-truncated cone portions 52b.

The flange portions 52a are plate-like members that are ring-like (doughnut-like) in plan view, having a fixed thickness and a fixed length (width) over the circumferential direction, and are secured, via a plurality of bolts (fastening members), between the joining surface of the front casing 3a (see FIG. 1) and the joining surface of the rear casing 3b (see FIG. 1) in an attachable/detachable manner.

The circular-truncated cone portions 52b are mortar-like members that have a fixed thickness and a fixed length (width) over the circumferential direction; that protrude backward (from the front casing 3a side toward the rear casing 3b side); and that connect the flange portions 52a and the stator-blade holding ring 8.

With the turbine 51 according to this embodiment, because the circular-truncated cone portions 52b are provided (formed) so as to have a fixed length (width) over the circumferential direction, it is possible to prevent asymmetrical differential thermal expansion of the support portion 52 (more specifically, the circular-truncated cone portions 52b), as well as deforming (tilting) of the support portion 52 (more specifically, the circular-truncated cone portions 52b) that are caused by a difference (pressure difference) between pressure that acts on a high-pressure side (right side in FIG. 7) surface of the support portion 52 (more specifically, the circular-truncated cone portions 52b) and pressure that acts on a low-pressure side (left side in FIG. 7) surface of the support portion 52 (more specifically, the circular-truncated cone portions 52b) and by having a high-temperature working fluid (for example, combustion gas or steam) pass through the inside of the stator-blade holding ring 8.

Furthermore, because deforming of the support portion 52 can be prevented, the tip clearance between tips (distal ends) of the turbine blades and the inner circumferential surface of the stator-blade holding ring 8 can be held constant, thereby making it possible to reduce leakage (tip leakage) from the tips of the turbine blades; and thus, the turbine efficiency (performance) can be enhanced, and contact between the tips of the turbine blades and the inner circumferential surface of the stator-blade holding ring 8 can also be prevented, making it possible to prevent damage to and breakage of the turbine blades and the turbine nozzles. Accordingly, the reliability of the turbine 51 can be enhanced.

Note that, in each embodiment described above, it is more preferable that the circular-truncated cone portions located at the lower-half portions have a greater plate thickness than the plate thickness of the circular-truncated cone portions located at the upper-half portion.

By doing so, the rigidity of the support portion can be further enhanced; the tip clearance between the tips (distal ends) of the turbine blades and the inner circumferential surface of the stator-blade holding ring can be held constant, thereby making it possible to further reduce leakage (tip leakage) from the tips of the turbine blades; and thus, turbine efficiency (performance) can be further enhanced, and contact between the tips of the turbine blades and the inner circumferential surface of the stator-blade holding ring can also be prevented, making it possible to prevent damage to and breakage of the turbine blades and the turbine nozzles. Accordingly, the reliability of the turbine can be further enhanced.

REFERENCE SIGNS LIST

• 1 turbine
• 2 turbine rotor
• 3 casing
• 3a front casing
• 3b rear casing
• 8 stator-blade holding ring
• 9 support portion
• 9a flange portion
• 9b circular-truncated cone portion
• 9c thick plate portion
• 22 support portion
• 22a flange portion
• 22b circular-truncated cone portion
• 23 outer circumferential surface
• 24 inner circumferential surface
• 31 turbine
• 32 support portion
• 32a flange portion
• 32b circular-truncated cone portion
• 33 joining surface
• 34 joining surface
• 41 turbine
• 42 ring
• 51 turbine
• 52 support portion
• 52a flange portion
• 52b circular-truncated cone portion

Claims

1. A turbine comprising:

a vertically divided casing that is divided into two portions in a longitudinal direction; and a support portion that supports a stator-blade holding ring disposed in the casing,

wherein, the support portion is provided with a flange portion that is secured between a joining surface of one portion of the casing and a joining surface of the other portion of the casing, being sandwiched therebetween, and a circular-truncated cone portion that connects the flange portion and the stator-blade holding ring, and

wherein a thick plate portion having a greater plate thickness than the plate thickness of the flange portion and the stator-blade holding ring is provided between the flange portion located at a lower-half portion and the stator-blade holding ring.

2. A turbine comprising:

a vertically divided casing that is divided into two portions in a longitudinal direction; and a support portion that supports a stator-blade holding ring disposed in the casing,

wherein, the support portion is provided with a flange portion that is secured between a joining surface of one portion of the casing and a joining surface of the other portion of the casing, being sandwiched therebetween, and a circular-truncated cone portion that connects the flange portion and the stator-blade holding ring, and

wherein the flange portion is formed so that the plate thickness thereof gradually increases from a radially outer side toward a radially inner side thereof, and so that the joining surfaces of the casing coincide with the joining surfaces of the flange portion.

3. A turbine comprising:

a vertically divided casing that is divided into two portions in a longitudinal direction; and a support portion that supports a stator-blade holding ring disposed in the casing,

wherein, the support portion is provided with a flange portion that is secured between a joining surface of one portion of the casing and a joining surface of the other portion of the casing, being sandwiched therebetween, and a circular-truncated cone portion that connects the flange portion and the stator-blade holding ring, and

wherein a ring fabricated using a high thermal expansion material as a constituent is provided between an outer circumferential surface of the circular-truncated cone portion and an inner circumferential surface of the front casing.

4. A turbine comprising:

a vertically divided casing that is divided into two portions in a longitudinal direction; and a support portion that supports a stator-blade holding ring disposed in the casing,

wherein, the support portion is provided with a flange portion that is secured between a joining surface of one portion of the casing and a joining surface of the other portion of the casing, being sandwiched therebetween, and a circular-truncated cone portion that connects the flange portion and the stator-blade holding ring, and

wherein the circular-truncated cone portion is formed so as to have a fixed length in a circumferential direction.

5. A turbine according to claim 1, wherein the plate thickness at a lower-half portion of the circular-truncated portion is greater than the plate thickness at an upper-half portion of the circular-truncated portion.

6. A turbine according to claim 2, wherein the plate thickness at a lower-half portion of the circular-truncated portion is greater than the plate thickness at an upper-half portion of the circular-truncated portion.

7. A turbine according to claim 3, wherein the plate thickness at a lower-half portion of the circular-truncated portion is greater than the plate thickness at an upper-half portion of the circular-truncated portion.

8. A turbine according to claim 4, wherein the plate thickness at a lower-half portion of the circular-truncated portion is greater than the plate thickness at an upper-half portion of the circular-truncated portion.