WO2011070636A1 - Turbine et pale de rotor de turbine - Google Patents

Turbine et pale de rotor de turbine Download PDF

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Publication number
WO2011070636A1
WO2011070636A1 PCT/JP2009/070466 JP2009070466W WO2011070636A1 WO 2011070636 A1 WO2011070636 A1 WO 2011070636A1 JP 2009070466 W JP2009070466 W JP 2009070466W WO 2011070636 A1 WO2011070636 A1 WO 2011070636A1
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WO
WIPO (PCT)
Prior art keywords
blade
turbine
tip shroud
rotor blade
shroud
Prior art date
Application number
PCT/JP2009/070466
Other languages
English (en)
Japanese (ja)
Inventor
耕一郎 飯田
Original Assignee
三菱重工業株式会社
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by 三菱重工業株式会社 filed Critical 三菱重工業株式会社
Priority to CN200980160732.4A priority Critical patent/CN102472109B/zh
Priority to US13/387,310 priority patent/US8920126B2/en
Priority to EP09852033.1A priority patent/EP2511476B1/fr
Priority to PCT/JP2009/070466 priority patent/WO2011070636A1/fr
Priority to KR1020127001317A priority patent/KR101323398B1/ko
Priority to KR1020137016497A priority patent/KR101411177B1/ko
Publication of WO2011070636A1 publication Critical patent/WO2011070636A1/fr

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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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
    • 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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/141—Shape, i.e. outer, aerodynamic form
    • F01D5/142—Shape, i.e. outer, aerodynamic form of the blades of successive rotor or stator blade-rows
    • F01D5/143—Contour of the outer or inner working fluid flow path wall, i.e. shroud or hub contour
    • 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/20—Specially-shaped blade tips to seal space between tips and stator
    • 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
    • F01D5/225—Blade-to-blade connections, e.g. for damping vibrations by shrouding
    • 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
    • F05D2250/10—Two-dimensional
    • F05D2250/18—Two-dimensional patterned
    • F05D2250/184—Two-dimensional patterned sinusoidal
    • 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
    • F05D2250/30—Arrangement of components
    • F05D2250/31—Arrangement of components according to the direction of their main axis or their axis of rotation
    • F05D2250/314—Arrangement of components according to the direction of their main axis or their axis of rotation the axes being inclined in relation to each other
    • 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
    • F05D2250/30—Arrangement of components
    • F05D2250/38—Arrangement of components angled, e.g. sweep angle
    • 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
    • F05D2250/70—Shape
    • F05D2250/71—Shape curved

Definitions

  • the present invention relates to a turbine and a turbine blade suitable for use in a turbine and a turbine blade, particularly a gas turbine and a steam turbine.
  • a turbine blade having a shroud (chip shroud) at the blade tip is known as a turbine rotor blade such as a gas turbine.
  • the shroud suppresses the vibration by causing the shrouds of adjacent turbine blades to come into contact with each other when vibration is generated in the turbine blade.
  • the shroud in the above-described turbine blade is reduced in weight from the viewpoint of strength.
  • the turbine blades arranged on the downstream side of the gas flow in the gas turbine in a situation where the turbine blades have become longer and the blade height has become higher due to the increase in capacity accompanying the recent increase in the output of the turbine.
  • the turbine blades arranged in the third and fourth stages of the turbine have a larger centrifugal load during rotation than the turbine blades arranged on the other upstream side, a little centrifugal load is applied.
  • the shroud has been reduced in weight to reduce it.
  • the weight of the shroud is reduced. Specifically, the shroud is reduced in weight by adopting a partial (partial) cover shape that covers only a part of the gap between the blade portion and the blade portion of the turbine blade as the shape of the shroud (non-shrouded).
  • Patent Document 1 a partial (partial) cover shape that covers only a part of the gap between the blade portion and the blade portion of the turbine blade as the shape of the shroud (non-shrouded).
  • Non-Patent Document 1 when the shroud has a partial cover shape as described above, it is described in Non-Patent Document 1 as compared with a turbine blade having a full cover-shaped shroud that covers the entire gap between the blade portion of the turbine blade and the blade portion. As described above, there is a problem that the performance of the turbine rotor blade and the turbine may deteriorate.
  • FIG. 12 is a schematic view of a partial cover-shaped shroud viewed from the outside in the radial direction.
  • FIG. 13 is a schematic diagram for explaining the flow of the working fluid around the turbine rotor blade having the partial cover-shaped shroud of FIG.
  • the turbine blade 504 in the case where the shape of the tip shroud 542 is recessed in the flow direction of the working fluid (the vertical direction in FIG. 12) between the turbine blades 504.
  • the flow of the surrounding working fluid will be described with reference to FIG.
  • FIG. 13 schematically illustrates the flow of the working fluid along the dotted line in FIG.
  • the flow of the working fluid on the back side of the moving blade 541 in the turbine moving blade 504 (the convex side of the curved moving blade 541) is schematically described.
  • a cavity portion 532 formed in a concave shape is formed at a position facing the turbine rotor blade 504 in the casing 503.
  • a plate-like shape extends toward the radially outer side and extends in the rotational direction of the turbine rotor blade 504 (perpendicular to the paper surface in FIG. 13). Seal fins 543 are provided.
  • the impinging working fluid returns to the inside of the casing 503 again, it peels off from the chip shroud 542 to form a separation vortex V.
  • the formation of the separation vortex V causes a problem that the flow loss of the working fluid occurs and the performance of the turbine rotor blade 504 and the like deteriorates.
  • the present invention has been made to solve the above-described problems, and provides a turbine and a turbine blade that can ensure the strength of the turbine blade and improve its performance.
  • a turbine according to an aspect of the present invention includes a moving blade rotating around a rotation axis in a main flow path of a substantially cylindrical casing whose diameter increases toward the downstream, and a distance in the rotation axis direction with respect to the moving blade. And forming a part of an annular shroud disposed at a radially outer end of the moving blade and the stationary blade disposed in the casing, and the rotation as the blade moves away from the rotating blade.
  • a tip shroud having a shorter length in the direction along the axis, and a cavity formed in a concave shape at a position facing the rotor blade in the casing, the tip shroud being housed therein, and the tip shroud.
  • An inclination angle ⁇ b with respect to the rotation axis on the inner peripheral surface of the casing is an inclination angle with respect to the rotation axis on the inner peripheral surface of the casing, and is disposed upstream of the mainstream. From the rear edge of the vanes, being greater than the average tilt angle ⁇ a to the cavity portion disposed downstream of the main flow.
  • the inclination angle ⁇ b related to the inner peripheral surface of the chip shroud is larger than the average inclination angle ⁇ a related to the inner peripheral surface of the casing.
  • the mainstream flowing in the direction of the approximate average inclination angle ⁇ a with respect to the rotation axis along the inner peripheral surface of the casing is in the direction of the approximate average inclination angle ⁇ b even in the region where the moving blade and the shroud are arranged.
  • the inclination angle ⁇ b related to the inner peripheral surface of the shroud is larger than the average inclination angle ⁇ a, the distance between the inner peripheral surface of the shroud and the main flow becomes wider toward the downstream side of the main flow.
  • the portion of the tip shroud away from the moving blade has a larger distance from the mainstream than the portion near the moving blade.
  • the above-described collision is unlikely to occur in a portion away from the moving blade in the tip shroud, which is likely to collide with the main flow, that is, a portion recessed downstream of the main flow in the tip shroud.
  • the occurrence of mainstream turbulence due to the collision with the tip shroud is avoided, and the performance of the turbine blade having the moving blade and the tip shroud and the performance of the turbine can be improved.
  • the tip shroud has a partial cover shape in which the length in the direction along the rotation axis of the tip shroud is shortened as the tip shroud moves away from the rotor blade, compared to the tip shroud of the full cover shape, The mass of the chip shroud can be reduced. Therefore, during the operation of the turbine, an increase in the centrifugal load acting on the moving blade can be suppressed, and the strength of the turbine moving blade having the moving blade and the tip shroud can be ensured.
  • the inclination angle ⁇ b related to the inner peripheral surface of the tip shroud may be configured to be 5 ° or more larger than the average inclination angle ⁇ a related to the inner peripheral surface of the casing. desirable.
  • the inclination angle ⁇ b related to the inner peripheral surface of the chip shroud is set to be 5 ° or more larger than the average inclination angle ⁇ a related to the inner peripheral surface of the casing, whereby the mainstream flowing in the casing and the chip shroud The collision can be avoided more reliably, and the performance of the turbine blade having the blade and the tip shroud and the performance of the turbine can be improved.
  • an interval that is a distance in a direction along the rotation axis from an upstream end portion of the mainstream in the tip shroud to an upstream end portion in the cavity portion. It is desirable that dx1 and a cord length dx2 that is a length in the direction along the rotational axis at the radially outer end of the moving blade satisfy a relational expression of dx1 ⁇ 0.5 ⁇ dx2. .
  • the distance dx1 is shorter than half of the cord length dx2, so that the collision between the main flow flowing in the casing and the tip shroud can be avoided more reliably, and the performance of the turbine blade having the moving blade and the tip shroud is achieved. In addition, the performance of the turbine can be improved.
  • the main flow flowing in the casing is less likely to flow into the gap between the cavity portion and the tip shroud, and the above-described portion in the portion of the tip shroud that is recessed downstream of the main flow. Collisions are less likely to occur.
  • the turbine rotor blade of the present invention constitutes a part of an annular shroud disposed at a radially outer end of the rotor blade that rotates about the rotation axis in the main flow path of the casing.
  • the convex portion of the moving blade on the inner peripheral surface of the tip shroud is disposed radially outside the portion on the concave side, so that the main flow flowing in the casing and the convex portion of the moving blade in the tip shroud are arranged.
  • the collision with the side portion can be avoided, and the performance of the turbine blade having the blade and the tip shroud and the performance of the turbine can be improved.
  • the main flow that flows on the convex side of the moving blade is more likely to flow into the gap between the cavity portion and the tip shroud and more likely to collide with the tip shroud, compared to the main flow that flows on the concave side of the moving blade. Therefore, as described above, by arranging the convex side portion of the rotor blade on the inner peripheral surface of the tip shroud on the radially outer side away from the mainstream, the collision between the tip shroud and the mainstream related to the convex side portion is prevented. It can be avoided.
  • the tip shroud has a partial cover shape in which the length in the direction along the rotation axis of the tip shroud is shortened as the tip shroud moves away from the rotor blade, compared to the tip shroud of the full cover shape, The mass of the chip shroud can be reduced. Therefore, when the turbine rotor blade rotates, an increase in the centrifugal load acting on the rotor blade can be suppressed, and the strength of the turbine rotor blade having the rotor blade and the tip shroud can be ensured.
  • the tip shroud in the vicinity of the blade of the tip shroud, extends radially outward from the concave side of the blade to the convex side. It is desirable that
  • the convex side portion of the moving blade in the tip shroud is inclined radially outward as it moves away from the moving blade, so that the main stream flowing in the casing and the convex side of the moving blade in the tip shroud Collisions with parts are avoided.
  • the convex portion of the blade in the tip shroud is farther from the main flow than the concave portion, collision between the main flow flowing in the casing and the convex portion of the blade in the tip shroud is avoided.
  • the fillet-shaped curvature that connects the convex portion of the blade and the tip shroud connects the concave portion of the blade and the tip shroud. It is desirable that the configuration be smaller than the fillet-shaped curvature.
  • the turbine of the present invention since the inclination angle ⁇ b related to the inner peripheral surface of the chip shroud is larger than the average inclination angle ⁇ a related to the inner peripheral surface of the casing, the collision between the main flow flowing in the casing and the chip shroud is prevented. Thus, there is an effect that the performance of the turbine blade having the blade and the tip shroud and the performance of the turbine can be improved.
  • the tip shroud has a partial cover shape that shortens the length of the tip shroud along the axis of rotation as it moves away from the blades, so that the centrifugal load acting on the blades increases during turbine operation. As a result, it is possible to secure the strength of the turbine rotor blade having the rotor blade and the tip shroud.
  • the convex side portion of the rotor blade on the inner peripheral surface of the tip shroud is arranged on the radially outer side than the concave side portion, whereby the mainstream flowing in the casing and the tip shroud The collision with the convex part of the moving blade is avoided, and the performance of the turbine moving blade having the moving blade and the tip shroud and the performance of the turbine can be improved.
  • the tip shroud has a partial cover shape in which the length in the direction along the axis of rotation of the tip shroud is reduced as the tip shroud moves away from the rotor blade, so that the centrifugal load acting on the rotor blade increases when the turbine rotor blade rotates. As a result, it is possible to secure the strength of the turbine rotor blade having the rotor blade and the tip shroud.
  • FIG. 6 is an AA cross-sectional view for explaining the flow of high-temperature fluid on the back side of the turbine rotor blade of FIG. 5.
  • FIG. 6 is a BB cross-sectional view for explaining the flow of high-temperature fluid on the ventral side of the turbine rotor blade of FIG. 5.
  • It is a schematic diagram explaining the flow of the high temperature fluid when the strong circulation flow is formed in the ventral side of the turbine rotor blade.
  • It is a schematic diagram explaining the shape of the turbine rotor blade in the turbine of this embodiment. It is the figure seen from the radial direction outer side explaining the shape of the chip
  • tip shroud of FIG. It is the schematic diagram which looked at the shroud of the partial cover shape from the radial direction outer side.
  • It is a schematic diagram explaining the flow of the working fluid around the turbine rotor blade which has the shroud of the partial cover shape of FIG.
  • FIG. 1 is a schematic diagram illustrating the configuration of a turbine according to the present embodiment.
  • the turbine 1 is rotatable around a rotation axis C together with a casing 3 in which a main flow path 2 in which a high-temperature fluid such as combustion gas flows is formed and a rotation shaft (not shown).
  • the arranged turbine rotor blade 4 and the turbine stationary blade 5 attached to the casing 3 are provided.
  • a turbine rotor blade 4 and a turbine stator blade 5 shown in FIG. 1 are a three-stage rotor blade and a three-stage stator blade arranged in the third stage from the upstream side of the main flow in the turbine 1.
  • the invention of the present application is described in the vicinity of the turbine rotor blade 4 and the turbine stationary blade 5, but is not limited to the periphery of the three-stage rotor blade and the three-stage stator blade.
  • the invention may be applied to the periphery of a four-stage moving blade and a four-stage stationary blade, and is not particularly limited.
  • the casing 3 is a member formed in a substantially cylindrical shape, in which the main flow channel 2, the turbine rotor blade 4, and the turbine stationary blade 5 are disposed.
  • the inner peripheral surface of the region of the casing 3 where the turbine rotor blade 4 and the turbine stationary blade 5 are arranged is from the upstream side to the downstream side (from the left side to the right side in FIG. 1). In this case, it is formed so as to be inclined outward in the radial direction around the rotation axis C.
  • the casing 3 is provided with a split ring 31 and a cavity portion 32.
  • the split ring 31 is a member that is disposed between the turbine rotor blade 4 and the turbine stationary blade 5 and constitutes a part of the casing 3, and is a member that is formed in a substantially annular shape around the rotation axis C. is there.
  • the cavity portion 32 is formed in a concave shape on the inner peripheral surface of the casing 3 facing the turbine rotor blade 4 toward the radially outer side with the rotation axis C as the center.
  • the cavity portion 32 is an annular groove portion formed on the inner peripheral surface of the casing 3.
  • the turbine stationary blades 5 are arranged along the cavity portion 32 at substantially equal intervals and extended radially inward.
  • a compressor for compressing external air or a fuel mixed with the compressed air is provided upstream of the region of the casing 3 where the turbine rotor blade 4 and the turbine stationary blade 5 are disposed (left side in FIG. 1).
  • a combustor or the like for performing combustion may be disposed and is not particularly limited.
  • the turbine rotor blade 4 includes a rotor blade 41 that is a blade portion extending in the radial direction, a tip shroud 42 disposed at the blade tip of the rotor blade 41, and seal fins 43 disposed on the outer peripheral surface of the tip shroud 42. And are provided.
  • FIG. 2 is a schematic diagram for explaining the shapes of tip shrouds, seal fins, and the like in the turbine rotor blade of FIG.
  • the moving blade 41 is a rotating blade that extends outward in the radial direction and is rotatably supported around the rotation axis C.
  • the moving blade 41 is a plate-like member having a blade-shaped cross section, and in this embodiment, the side of the surface curved in a convex shape (left side in FIG. 2) is curved in a concave shape on the back side (convex side).
  • the side of the surface (the right side in FIG. 2) will be described as the ventral side (concave side).
  • the tip shroud 42 constitutes an annular shroud centered on the rotation axis C together with tip shrouds 45 provided on the other turbine blades 4.
  • the tip shroud 42 viewed from the outside in the radial direction has a dimension in the direction along the rotation axis C (vertical direction in FIG. 2) in the vicinity of the rotor blade 41, in other words, in the direction along the mainstream flow.
  • a certain width is the largest, and the width becomes narrower as it moves away from the rotor blade 41 along the circumferential direction (left-right direction in FIG. 2).
  • the chip shroud 42 is in contact with another adjacent chip shroud 42 at a portion where the width is narrowed.
  • the seal fin 43 suppresses the bypass flow that flows by narrowing the gap between the tip shroud 42 of the rotor blade and the cavity portion 32 to form a Tip clearance.
  • the seal fins 43 are ring plate-like members extending from the outer peripheral surface of the tip shroud 42 toward the radially outer side.
  • the average inclination angle ⁇ a related to the inner peripheral surface of the casing 3 includes an inner peripheral surface at the rear edge of the turbine stationary blade 5 and an inner peripheral surface at the downstream side end of the split ring 31. This is the angle between the connected mean inclination line G and the rotation axis C.
  • the inclination angle ⁇ b related to the inner peripheral surface of the tip shroud 42 is an angle between the inner peripheral surface of the tip shroud 42 and the rotation axis C.
  • the distance Lb between the upstream end portion 42b of the tip shroud 42 away from the moving blade 41 and the above-described average inclination line G is the upstream side of the tip shroud 42 in the vicinity of the moving blade 41.
  • the distance La is set to be longer than the distance La between the end portion 42a and the above-described average inclined line G.
  • the upstream end 42a is disposed on the radially outer side than the above-described average inclination line G, and the upstream end 42b is further disposed on the radially outer side.
  • the distance dx1 is the distance between the upstream end 42a of the tip shroud 42 and the upstream end of the cavity 32, in other words, the distance between the upstream end 42a and the downstream end of the split ring 31.
  • the cord length dx2 is the length in the direction along the rotation axis C at the radially outer end of the rotor blade 41.
  • the distance dx1 and the code length dx2 described above satisfy at least the relationship of the following expression (3). dx1 ⁇ 0.5 ⁇ dx2 (3) Furthermore, it is preferable that the relationship of the following formula (4) is satisfied. 0.3 ⁇ dx2 ⁇ dx1 ⁇ 0.5 ⁇ dx2 (4) Desirably, it is more preferable to satisfy
  • equation (5). dx1 0.45 ⁇ dx2 (5)
  • the flow of the high-temperature fluid in the turbine 1 having the above configuration will be described.
  • the high-temperature fluid flowing through the main flow path 2 of the turbine 1 passes between the turbine stationary blades 5, and then travels along the inner peripheral surface of the casing 3 toward the downstream turbine blade 4. Flowing.
  • ⁇ a the average inclination angle related to the inner peripheral surface of the casing 3, it flows downstream while enlarging the cross-sectional area of the flow path.
  • FIG. 3 is a schematic diagram for explaining the flow of a high-temperature fluid around the turbine rotor blade in FIG. 1.
  • a part of the high-temperature fluid that flows into the cavity portion 32 from the split ring 31 flows into the cavity portion 32 from the gap between the upstream end 42 b of the tip shroud 42 and the split ring 31 and circulates.
  • the other high-temperature fluid flows downstream along the inner peripheral surface of the tip shroud 42.
  • the tip shroud 42 is disposed inside the cavity portion 32, in other words, radially outside the inner peripheral surface of the split ring 31, so that the high-temperature fluid can be used as the tip shroud. It flows downstream without colliding with 42.
  • the inclination angle ⁇ b related to the inner peripheral surface of the chip shroud 42 is larger than the average inclination angle ⁇ a related to the inner peripheral surface of the casing 3, the high-temperature fluid flowing in the casing 3 and the chip shroud 42.
  • the performance of the turbine rotor blade 4 having the rotor blade 41 and the tip shroud 42 and the performance of the turbine 1 can be improved.
  • the main flow that flows in the direction of the approximate average inclination angle ⁇ a with respect to the rotation axis C along the inner peripheral surface of the casing 3 is substantially the average inclination angle ⁇ b even in the region where the turbine rotor blade 4 is disposed. Flowing in the direction of.
  • the inclination angle ⁇ b related to the inner peripheral surface of the chip shroud 42 is larger than the average inclination angle ⁇ a, the distance between the inner peripheral surface of the chip shroud 42 and the above-described main stream becomes closer to the downstream side of the high-temperature fluid. Spacing increases.
  • a portion of the tip shroud that is away from the moving blade 41 has a larger distance from the mainstream than the portion near the moving blade 41.
  • the above-described collision is unlikely to occur at the portion of the tip shroud 42 that is likely to collide with the mainstream, away from the moving blade 41, that is, at the upstream end 42b.
  • the occurrence of mainstream turbulence due to the collision with the tip shroud 42 is avoided, and the performance of the turbine rotor blade 4 and the performance of the turbine 1 can be improved.
  • the tip shroud 42 has a partial cover shape in which the length in the direction along the rotational axis C of the tip shroud 42 is reduced as the tip shroud 42 moves away from the moving blade 41, the tip shroud 42 has a full cover shape. In comparison, the mass of the tip shroud 42 can be reduced. Therefore, when the turbine 1 is operated, an increase in the centrifugal load acting on the rotor blade 41 can be suppressed, and the strength of the turbine rotor blade 4 can be ensured.
  • the high-temperature fluid flowing in the casing 3 is less likely to flow into the gap between the cavity portion 32 and the tip shroud 42, and the downstream side of the main flow in the tip shroud 42 is reduced.
  • the above-described collision in the recessed portion is less likely to occur.
  • FIG. 4 is a schematic diagram for explaining the shape of the turbine rotor blade in the turbine of the present embodiment.
  • symbol is attached
  • the turbine rotor blade 104 in the turbine 101 of the present embodiment includes a rotor blade 41 that is a blade portion extending in the radial direction, and a tip shroud 142 disposed at the tip of the rotor blade 41.
  • the seal fin 43 and the contact rib 145 are provided on the outer peripheral surface of the chip shroud 142.
  • FIG. 5 is a view seen from the upstream side of the flow of the high-temperature fluid for explaining the shape of the tip shroud of FIG. 6 is a diagram viewed from the radially outer side for explaining the shape of the chip shroud of FIG.
  • the tip shroud 142 and the tip shroud 142 provided on the other plurality of turbine rotor blades 104 constitute an annular shroud centered on the rotation axis C.
  • the tip shroud 142 viewed from the upstream side of the flow of the high-temperature fluid is located near the moving blade 41 from the ventral side to the back side (from the left side to the right side in FIG. 5). Inclined radially outward (upper side in FIG. 5). On the other hand, the tip shroud 142 is inclined in the opposite direction to the vicinity of the rotor blade 41 so as to form a smooth inner peripheral surface together with the adjacent tip shroud 142 at the end portion away from the rotor blade 41. .
  • the inner peripheral surface of the tip shroud 142 in the vicinity of the back side of the moving blade 41 (right side in FIG. 5) is more than the inner peripheral surface in the vicinity of the ventral side (left side in FIG. 5). Arranged radially outside.
  • the tip shroud 142 viewed from the outside in the radial direction has a dimension in the direction along the rotation axis C in the vicinity of the moving blade 41 (up and down direction in FIG. 5), in other words, in the direction along the mainstream flow.
  • a certain width is the widest, and the width becomes narrower as it moves away from the moving blade 41 along the circumferential direction (left-right direction in FIG. 5).
  • the tip shroud 142 is in contact with another adjacent tip shroud 142 at a portion where the width is narrowed.
  • the contact rib 145 is a plate-like member provided at an end portion of the chip shroud 142 where the chip shrouds 142 come into contact with each other.
  • the contact rib 145 extends radially outward from the outer peripheral surface of the chip shroud 142 and has a rotational axis C. It extends along. By configuring in this way, adjacent contact ribs 145 are in surface contact.
  • FIG. 7 is a cross-sectional view taken along line AA for explaining the flow of the high-temperature fluid on the back side of the turbine rotor blade of FIG.
  • a high-temperature fluid flows as shown in FIG. That is, the portion of the tip shroud 142 in the vicinity of the back side of the moving blade 41 is disposed radially outside the portion in the vicinity of the ventral side, in other words, away from the flow of the high-temperature fluid.
  • the high-temperature fluid that has flowed from the region into the region of the turbine blade 104 flows smoothly downstream without colliding with the tip shroud 142.
  • FIG. 8 is a cross-sectional view taken along the line BB for explaining the flow of the high-temperature fluid on the ventral side of the turbine rotor blade of FIG.
  • high-temperature fluid flows near the ventral side of the moving blade 41 in the turbine moving blade 104. That is, since the portion of the tip shroud 142 near the ventral side of the rotor blade 41 is disposed radially inward compared to the portion near the back side, in other words, close to the flow of the high-temperature fluid, The high-temperature fluid that has flowed into the region of the turbine rotor blade 104 from the region flows smoothly downstream without forming a strong circulation flow (see FIG. 9) in the cavity portion 32.
  • FIG. 9 is a schematic diagram illustrating the flow of the high-temperature fluid when a strong circulation flow is formed on the ventral side of the turbine rotor blade.
  • a strong circulating flow S is formed inside the cavity portion 32, in other words, between the split ring 31 and the turbine rotor blade 104. Due to this circulating flow S, the flow of the high-temperature fluid is bent, and the performance of the turbine rotor blade 104 is degraded.
  • the flow velocity of the high-temperature fluid in the vicinity of the back side is faster. Therefore, even if the tip shroud 142 near the back side of the moving blade 41 is arranged on the radially outer side, it flows smoothly downstream without forming a strong circulating flow as in the vicinity of the ventral side. On the other hand, even if the vicinity of the ventral side of the moving blade 41 in the tip shroud 142 is disposed radially inward, the flow of the high-temperature fluid does not collide with the tip shroud 142 as in the vicinity of the back side, so It flows downstream.
  • the portion of the tip shroud 142 on the back side of the moving blade 41 is disposed radially outside the portion on the ventral side, so that the high-temperature fluid flowing in the casing 3 and the moving blade in the tip shroud 142 can be obtained. Collision with the back side portion of 41 is avoided, and the performance of the turbine rotor blade 104 and the performance of the turbine 101 can be improved.
  • the high-temperature fluid flowing on the back side of the moving blade 41 is more likely to flow into the gap between the cavity portion 32 and the tip shroud 142 than the high-temperature fluid flowing on the ventral side of the moving blade 41, and the tip shroud 142. Easy to collide with. Therefore, as described above, by disposing the back side portion of the rotor blade in the tip shroud 142 on the radially outer side away from the high temperature fluid, the tip shroud 142 related to the back side portion and the flow of the high temperature fluid Collisions can be avoided.
  • FIG. 10 is a schematic diagram for explaining the shape of the turbine rotor blade in the turbine of the present embodiment.
  • FIG. 11 is a diagram viewed from the outside in the radial direction for explaining the shape of the chip shroud of FIG.
  • symbol is attached
  • the turbine blade 204 in the turbine 201 of the present embodiment includes a blade 41 that is a blade portion extending in the radial direction, and a tip disposed at the blade tip of the blade 41.
  • a shroud 242 and seal fins 43 and contact ribs 145 disposed on the outer peripheral surface of the tip shroud 242 are provided.
  • the tip shroud 242 constitutes an annular shroud around the rotation axis C together with the tip shroud 242 provided on the other plurality of turbine blades 204.
  • the back side surface (the right side surface in FIG. 10) of the moving blade 41 and the inner peripheral surface of the tip shroud 242 are smoothly connected by a back side fillet 243.
  • the ventral side surface (the left side surface in FIG. 10) of the moving blade 41 and the inner peripheral surface of the tip shroud 242 are smoothly connected by the ventral fillet 244.
  • the dorsal fillet 243 has a smaller radius of curvature than the ventral fillet 244. Therefore, in the vicinity of the moving blade 41, the inner peripheral surface of the tip shroud 242 in the vicinity of the back side of the moving blade 41 is disposed on the radially outer side (upper side in FIG. 10) than the inner peripheral surface of the tip shroud 242 in the vicinity of the abdominal side. Is done.
  • ventral fillet 244 has a larger radius of curvature than the dorsal fillet 243. Therefore, in the vicinity of the moving blade 41, the inner peripheral surface of the tip shroud 242 near the ventral side of the moving blade 41 is radially inward (lower side in FIG. 10) with respect to the inner peripheral surface of the tip shroud 242 in the vicinity of the back side. Be placed.
  • the tip shroud 242 viewed from the outside in the radial direction has a dimension along the rotation axis C in the vicinity of the moving blade 41 (up and down direction in FIG. 11), in other words, a dimension along the mainstream flow.
  • a certain width is the widest, and the width becomes narrower as it moves away from the moving blade 41 along the circumferential direction (left-right direction in FIG. 11).
  • chip shroud 242 is in contact with another adjacent chip shroud 242 at a portion where the width is narrowed. As shown in FIG. 11, the end portion of the tip shroud 242 that contacts the other tip shroud 242 is disposed near the back surface of the moving blade 41 and away from the ventral surface.
  • the curvature radius of the dorsal fillet 243 is made smaller than the curvature radius of the ventral fillet 244, so that the back surface of the moving blade 41 on the inner peripheral surface of the tip shroud 242 is near the moving blade 41.
  • the side portion is disposed radially outside the ventral portion. Therefore, it is possible to avoid collision between the high-temperature fluid flowing in the casing 3 and the back side portion of the rotor blade 41 in the tip shroud 242.
  • the present invention has been described by applying to the turbine rotor blade of a gas turbine.
  • the present invention is not limited to the turbine rotor blade of a gas turbine, and the turbine of various turbines such as a steam turbine. Applicable to moving blades.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

L'invention divulgue une turbine et une pale de rotor de turbine qui peuvent améliorer la performance tout en assurant la résistance de la pale de rotor de turbine. Ladite turbine comprend: une pale de rotor (4) qui tourne autour d'un axe de rotation (C) à l'intérieur d'un canal d'écoulement principal (2) dans un boîtier (3); une aube de stator (5) qui est disposée à l'intérieur du boîtier (3); un carénage de pointe (42) qui est disposé sur la pointe radialement extérieure de la pale de rotor (4), la longueur dudit carénage de pointe le long de l'axe de rotation (C) diminuant au fur et à mesure de la séparation par rapport à la pale de rotor (4); et une section de cavité (32) qui est formée à l'intérieur du boîtier (3) à une position opposée à la pale de rotor (4). Le carénage de pointe (42) s'agence à l'intérieur de la section de cavité. L'angle d'inclinaison (?b) de la surface intérieure du carénage de pointe (42) est plus grand que l'angle d'inclinaison de la surface intérieure du boîtier (3), qui est également l'angle d'inclinaison moyen (?a) entre le bord de fuite de l'aube de stator (5), qui est disposé en amont par rapport à l'écoulement principal, et la section de cavité (32), qui est disposée en aval par rapport à l'écoulement principal.
PCT/JP2009/070466 2009-12-07 2009-12-07 Turbine et pale de rotor de turbine WO2011070636A1 (fr)

Priority Applications (6)

Application Number Priority Date Filing Date Title
CN200980160732.4A CN102472109B (zh) 2009-12-07 2009-12-07 涡轮机及涡轮机动叶片
US13/387,310 US8920126B2 (en) 2009-12-07 2009-12-07 Turbine and turbine rotor blade
EP09852033.1A EP2511476B1 (fr) 2009-12-07 2009-12-07 Turbine
PCT/JP2009/070466 WO2011070636A1 (fr) 2009-12-07 2009-12-07 Turbine et pale de rotor de turbine
KR1020127001317A KR101323398B1 (ko) 2009-12-07 2009-12-07 터빈 및 터빈 동익
KR1020137016497A KR101411177B1 (ko) 2009-12-07 2009-12-07 터빈 및 터빈 동익

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/JP2009/070466 WO2011070636A1 (fr) 2009-12-07 2009-12-07 Turbine et pale de rotor de turbine

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WO2011070636A1 true WO2011070636A1 (fr) 2011-06-16

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US (1) US8920126B2 (fr)
EP (1) EP2511476B1 (fr)
KR (2) KR101323398B1 (fr)
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WO (1) WO2011070636A1 (fr)

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JP2013148086A (ja) * 2012-01-20 2013-08-01 General Electric Co <Ge> ターボ機械ブレード先端シュラウド
JP2018135846A (ja) * 2017-02-23 2018-08-30 三菱重工業株式会社 軸流回転機械

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US20170130596A1 (en) * 2015-11-11 2017-05-11 General Electric Company System for integrating sections of a turbine
KR102000281B1 (ko) * 2017-10-11 2019-07-15 두산중공업 주식회사 압축기 및 이를 포함하는 가스 터빈
JP7017446B2 (ja) * 2018-03-20 2022-02-08 本田技研工業株式会社 軸流圧縮機
JP6986155B2 (ja) * 2018-06-19 2021-12-22 三菱パワー株式会社 タービン動翼、ターボ機械及びコンタクト面製造方法
JP7380846B2 (ja) 2020-03-30 2023-11-15 株式会社Ihi 二次流れ抑制構造
CN112099544A (zh) * 2020-09-04 2020-12-18 上海交通大学 汽轮机末级涡轮叶片振动控制系统
JP7352534B2 (ja) * 2020-11-25 2023-09-28 三菱重工業株式会社 蒸気タービン動翼、蒸気タービン動翼の製造方法及び改造方法

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JP2018135846A (ja) * 2017-02-23 2018-08-30 三菱重工業株式会社 軸流回転機械

Also Published As

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EP2511476B1 (fr) 2017-11-22
US8920126B2 (en) 2014-12-30
CN102472109A (zh) 2012-05-23
KR20130084968A (ko) 2013-07-26
EP2511476A4 (fr) 2015-08-19
EP2511476A1 (fr) 2012-10-17
US20120121394A1 (en) 2012-05-17
KR101411177B1 (ko) 2014-06-23
CN102472109B (zh) 2015-04-01
KR101323398B1 (ko) 2013-10-29
KR20130085057A (ko) 2013-07-26

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