US20110176918A1 - Turbine - Google Patents

Turbine Download PDF

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Publication number
US20110176918A1
US20110176918A1 US13/063,972 US200913063972A US2011176918A1 US 20110176918 A1 US20110176918 A1 US 20110176918A1 US 200913063972 A US200913063972 A US 200913063972A US 2011176918 A1 US2011176918 A1 US 2011176918A1
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United States
Prior art keywords
casing
circular
turbine
stator
support portion
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Abandoned
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US13/063,972
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English (en)
Inventor
Yukihiro Otani
Naoto Tochitani
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Mitsubishi Heavy Industries Ltd
Original Assignee
Mitsubishi Heavy Industries Ltd
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Filing date
Publication date
Application filed by Mitsubishi Heavy Industries Ltd filed Critical Mitsubishi Heavy Industries Ltd
Assigned to MITSUBISHI HEAVY INDUSTRIES, LTD. reassignment MITSUBISHI HEAVY INDUSTRIES, LTD. ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: OTANI, YUKIHIRO, TOCHITANI, NAOTO
Publication of US20110176918A1 publication Critical patent/US20110176918A1/en
Abandoned legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/246—Fastening of diaphragms or stator-rings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/243—Flange connections; Bolting arrangements
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/26—Double casings; Measures against temperature strain in casings
    • F01D25/265—Vertically split casings; Clamping arrangements therefor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/60—Assembly methods
    • F05D2230/64—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins
    • F05D2230/642—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins using maintaining alignment while permitting differential dilatation
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/20—Three-dimensional
    • F05D2250/23—Three-dimensional prismatic
    • F05D2250/232—Three-dimensional prismatic conical

Definitions

  • 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.
  • Patent Literature 1 Known turbines that obtain a rotational force using a high-temperature working fluid include, for example, the disclosure in Patent Literature 1.
  • 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 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.
  • 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.
  • a high-temperature working fluid for example, combustion gas or steam
  • a high-temperature working fluid 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.
  • 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.
  • 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).
  • 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.
  • a high-temperature working fluid for example, combustion gas or steam
  • 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.
  • 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).
  • 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.
  • a high-temperature working fluid for example, combustion gas or steam
  • 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.
  • 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.
  • 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.
  • a high-temperature working fluid for example, combustion gas or steam
  • 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.
  • 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.
  • a high-temperature working fluid for example, combustion gas or steam
  • 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.
  • 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.
  • 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.
  • 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.
  • 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.
  • FIGS. 1 to 3 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
  • 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.
  • 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 3 a located on the right side in FIG. 1 and a rear casing 3 b located on the left side in FIG. 1 .
  • flange portions 9 a of a support portion 9 that supports a stator-blade holding ring 8 are configured so as to be sandwiched between the front casing 3 a and the rear casing 3 b.
  • 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.
  • the support portion 9 includes the flange portions 9 a, circular-truncated cone portions 9 b, and thick plate portions 9 c.
  • the flange portions 9 a 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 3 a (see FIG. 1 ) and a joining surface of the rear casing 3 b (see FIG. 1 ) in an attachable/detachable manner.
  • the circular-truncated cone portions 9 b 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 3 a side toward a rear casing 3 b side); that connect the flange portions 9 a and the stator-blade holding ring 8 at upper-half portions thereof; and that connect the thick plate portions 9 c and the stator-blade holding ring 8 at lower-half portions thereof.
  • the thick plate portions 9 c 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 9 a and the circular-truncated cone portions 9 b.
  • the “plate thickness” of the thick plate portions 9 c 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 .
  • the thick plate portions 9 c 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 9 b ) 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 9 b ) 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 9 b ).
  • the thick plate portions 9 c 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 9 b ) 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 9 b ) caused by this asymmetrical differential thermal expansion.
  • a high-temperature working fluid for example, combustion gas or steam
  • 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.
  • 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 is provided with flange portions 22 a and circular-truncated cone portions 22 b.
  • the flange portions 22 a 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 3 a and the joining surface of the rear casing 3 b in an attachable/detachable manner.
  • the circular-truncated cone portions 22 b are mortar-like members that have a fixed thickness over the circumferential direction; that protrude backward (from the front casing 3 a side toward the rear casing 3 b side); and that connect the flange portions 22 a and the stator-blade holding ring 8 in the circumferential direction.
  • outer circumferential surfaces (circumferential surfaces at the radially outer side) 23 of the circular-truncated cone portions 22 b are provided (formed) so as to be located in the vicinity of inner circumferential surfaces 24 of the front casing 3 a and the rear casing 3 b, that is, so as to be located as close as possible to the inner circumferential surfaces 24 of the front casing 3 a and the rear casing 3 b.
  • the turbine 21 With the turbine 21 according to this embodiment, deforming (tilting) of the support portion 22 (more specifically, the circular-truncated cone portions 22 b ) 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 is provided with flange portions 32 a and circular-truncated cone portions 32 b.
  • the flange portions 32 a 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 3 a and the joining surface of the rear casing 3 b in an attachable/detachable manner.
  • the joining surfaces 33 of the front casing 3 a in this embodiment are provided (formed) so as to coincide with (come in contact with) joining surfaces 34 of the flange portions 32 a.
  • the circular-truncated cone portions 32 b are mortar-like members that have a fixed thickness over the circumferential direction; that protrude backward (from the front casing 3 a side toward the rear casing 3 b side); and that connect the flange portions 32 a and the stator-blade holding ring 8 .
  • the flange portions 32 a 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 32 b ) 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 32 b ) 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 32 b ).
  • the flange portions 32 a 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 32 b ) 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 32 b ) caused by this asymmetrical differential thermal expansion.
  • a high-temperature working fluid for example, combustion gas or steam
  • 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.
  • the joining surfaces 33 of the front casing 3 a and the joining surfaces 34 of the flange portions 32 a 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 3 a 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 22 b and the inner circumferential surfaces 24 of the front casing 3 a. 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.
  • a high-thermal-expansion material for example, SUS304
  • 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 .
  • 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 22 b 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 3 a 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 22 b and the inner circumferential surfaces 24 of the front casing 3 a is completely filled with the ring 42 , without any gap.
  • a high-temperature working fluid for example, combustion gas or steam
  • the support portion 22 (more specifically, the circular-truncated cone portions 22 b ) to deform (tilt) due to a pressure difference or differential thermal expansion during turbine operation
  • deforming (tilting) of the support portion 22 is prevented by the ring 42 disposed (interposed) between the outer circumferential surfaces 23 of the circular-truncated cone portions 22 b and the inner circumferential surfaces 24 of the front casing 3 a.
  • the turbine 42 because deforming (tilting) of the support portion 22 (more specifically, the circular-truncated cone portions 22 b ) 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 is provided with flange portions 52 a and circular-truncated cone portions 52 b.
  • the flange portions 52 a 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 3 a (see FIG. 1 ) and the joining surface of the rear casing 3 b (see FIG. 1 ) in an attachable/detachable manner.
  • the circular-truncated cone portions 52 b 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 3 a side toward the rear casing 3 b side); and that connect the flange portions 52 a and the stator-blade holding ring 8 .
  • the circular-truncated cone portions 52 b 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 52 b ), as well as deforming (tilting) of the support portion 52 (more specifically, the circular-truncated cone portions 52 b ) 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 52 b ) and pressure that acts on a low-pressure side (left side in FIG.
  • 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.
  • 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.
  • 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.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
US13/063,972 2009-01-30 2009-08-10 Turbine Abandoned US20110176918A1 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
JP2009-019797 2009-01-30
JP2009019797A JP2010174795A (ja) 2009-01-30 2009-01-30 タービン
PCT/JP2009/064108 WO2010087044A1 (fr) 2009-01-30 2009-08-10 Turbine

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US20110176918A1 true US20110176918A1 (en) 2011-07-21

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US13/063,972 Abandoned US20110176918A1 (en) 2009-01-30 2009-08-10 Turbine

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US (1) US20110176918A1 (fr)
EP (1) EP2385222A4 (fr)
JP (1) JP2010174795A (fr)
CN (1) CN102165143A (fr)
WO (1) WO2010087044A1 (fr)
ZA (1) ZA201101813B (fr)

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US20120247123A1 (en) * 2011-03-28 2012-10-04 Rolls-Royce Plc Securing system
EP3214277A1 (fr) * 2016-02-23 2017-09-06 United Technologies Corporation Systèmes pour renforcer des boîtiers sur des moteurs à turbine à gaz
US11359513B2 (en) 2017-02-28 2022-06-14 Siemens Energy Global GmbH & Co. KG Turbine casing and method for assembling a turbine having a turbine casing

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CN106425283A (zh) * 2016-11-30 2017-02-22 哈尔滨理工大学 汽轮机转子旋转工作台
CN114542212A (zh) * 2022-03-09 2022-05-27 中国船舶重工集团公司第七0三研究所 一种新型船用汽轮机倒车汽缸

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US6213710B1 (en) * 1996-04-11 2001-04-10 Siemens Aktiengesellschaft Method and apparatus for thrust compensation on a turbomachine
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US5044881A (en) * 1988-12-22 1991-09-03 Rolls-Royce Plc Turbomachine clearance control
US6213710B1 (en) * 1996-04-11 2001-04-10 Siemens Aktiengesellschaft Method and apparatus for thrust compensation on a turbomachine
US6305901B1 (en) * 1997-01-14 2001-10-23 Siemens Aktiengesellschaft Steam turbine
US20080267768A1 (en) * 2007-02-28 2008-10-30 Snecma High-pressure turbine of a turbomachine

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20120247123A1 (en) * 2011-03-28 2012-10-04 Rolls-Royce Plc Securing system
EP3214277A1 (fr) * 2016-02-23 2017-09-06 United Technologies Corporation Systèmes pour renforcer des boîtiers sur des moteurs à turbine à gaz
US11359513B2 (en) 2017-02-28 2022-06-14 Siemens Energy Global GmbH & Co. KG Turbine casing and method for assembling a turbine having a turbine casing

Also Published As

Publication number Publication date
EP2385222A4 (fr) 2012-07-11
JP2010174795A (ja) 2010-08-12
ZA201101813B (en) 2012-10-31
EP2385222A1 (fr) 2011-11-09
WO2010087044A1 (fr) 2010-08-05
CN102165143A (zh) 2011-08-24

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