EP2241723A1 - Turbine blade-cascade end wall - Google Patents

Turbine blade-cascade end wall Download PDF

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Publication number
EP2241723A1
EP2241723A1 EP08872470A EP08872470A EP2241723A1 EP 2241723 A1 EP2241723 A1 EP 2241723A1 EP 08872470 A EP08872470 A EP 08872470A EP 08872470 A EP08872470 A EP 08872470A EP 2241723 A1 EP2241723 A1 EP 2241723A1
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EP
European Patent Office
Prior art keywords
turbine
blade
blades
stationary blade
stationary
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.)
Granted
Application number
EP08872470A
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German (de)
French (fr)
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EP2241723A4 (en
EP2241723B1 (en
Inventor
Yasuro Sakamoto
Eisaku Ito
Susumu Wakazono
Takashi Hiyama
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Mitsubishi Power Ltd
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Mitsubishi Heavy Industries Ltd
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Publication date
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Publication of EP2241723A1 publication Critical patent/EP2241723A1/en
Publication of EP2241723A4 publication Critical patent/EP2241723A4/en
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    • 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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
    • 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
    • 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
    • F01D5/141—Shape, i.e. outer, aerodynamic form
    • F01D5/145—Means for influencing boundary layers or secondary circulations
    • 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
    • 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
    • F05D2250/711—Shape curved convex

Definitions

  • the present invention employs the following solutions. defining 0% Cax as a leading edge position of the turbine stationary blades or the turbine moving blades in an axial direction and 100% Cax as a trailing edge position of the turbine stationary blades or the turbine moving blades in the axial direction, and defining 0% pitch as a position on a pressure side surface of the turbine stationary blades or the turbine moving blades, and 100% pitch as a position on a suction side surface of a turbine stationary blade or a turbine moving blade facing the pressure side surface of the turbine stationary blade or the turbine moving blade, a convex portion, which is gently swollen as a whole, which has an apex at a position of 0 to 20 % pitch at a position of 5 to 25 % Cax, which gently slopes from this apex toward a downstream side and the suction side surface of the adjacently disposed turbine stationary blade or turbine moving blade, and which slopes slightly steeply from the apex toward an upstream side, is
  • the depth (degree of concavity) of the bottom point P5 of this second concave portion 41 is set at 5 % to 15 % (about 9.4 % in this embodiment) of the axial chord length of the fourth-stage stationary blade B2 (length of the fourth-stage stationary blade B2 in the axial direction).
  • a turbine blade cascade endwall has been described as exemplified in the third-stage stationary-blade tip endwall, the third-stage stationary-blade hub endwall, the fourth-stage stationary-blade tip endwall, and the fourth-stage stationary-blade hub endwall; however, the present invention is not limited thereto, and it can be applied to a hub endwall of turbine moving blades, a tip endwall of turbine moving blades, a stationary-blade tip endwall of other stages, or a stationary-blade tip endwall of other stages.

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  • Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Hydraulic Turbines (AREA)

Abstract

Provided is a turbine blade cascade endwall that is capable of reducing crossflow and is capable of reducing secondary-flow loss that occurs in association with the crossflow, therefore being capable of achieving enhanced turbine performance. A convex portion (11) that is gently swollen as a whole, that has an apex (P1) at a position of 0 to 20 % pitch in a position of 5 to 25 % Cax, that gently slopes from this apex (P1) toward a downstream side and a suction side surface of an adjacently disposed turbine stationary blade (B1) or turbine moving blade, and that slopes slightly steeply from the apex (P1) toward an upstream side is provided between one turbine stationary blade (B1) or turbine moving blade and another turbine stationary blade (B1) or turbine moving blade disposed adjacent to one turbine stationary blade (B1) or turbine moving blade.

Description

    Technical Field
  • The present invention relates to a turbine blade cascade endwall.
    • Background Art
  • On a turbine blade cascade endwall in a turbine serving as a motive power generator that obtains motive power by converting kinetic energy of a fluid to rotational motion, a so-called "crossflow (secondary flow)" occurs from the pressure side of one turbine blade to the suction side of an adjacent turbine blade.
    In order to enhance the turbine performance, it is necessary to reduce this crossflow and to reduce secondary-flow loss that occurs in association with the crossflow.
  • Therefore, as a turbine blade cascade endwall that reduces such secondary-flow loss associated with crossflow to improve turbine performance, one having non-axisymmetric irregularities formed thereon has been known (for example, see Patent Citation 1).
    • Disclosure of Invention
  • In a turbine blade cascade endwall disclosed in the above-described Patent Citation, a concave portion is formed on a suction-side trailing edge of one turbine blade and a convex portion is formed on a pressure-side trailing edge of an adjacent turbine blade.
    However, in the convex portion formed on the pressure-side trailing edge, static pressure declines thereat, and a discharge angle of a blade outlet ends up increasing, which deteriorates the performance of a blade cascade located downstream of a blade cascade having irregularities, thereby posing the risk of decreasing the overall performance of a turbine having a plurality of blade cascades.
  • The present invention has been conceived in light of above-described circumstances, and an object thereof is to provide a turbine blade cascade endwall that is capable of reducing a crossflow and that is also capable of reducing secondary-flow loss that occurs in association with the crossflow, thus being capable of achieving enhanced turbine performance.
  • In order to solve the above-described problems, the present invention employs the following solutions.
    defining 0% Cax as a leading edge position of the turbine stationary blades or the turbine moving blades in an axial direction and 100% Cax as a trailing edge position of the turbine stationary blades or the turbine moving blades in the axial direction, and defining 0% pitch as a position on a pressure side surface of the turbine stationary blades or the turbine moving blades, and 100% pitch as a position on a suction side surface of a turbine stationary blade or a turbine moving blade facing the pressure side surface of the turbine stationary blade or the turbine moving blade, a convex portion, which is gently swollen as a whole, which has an apex at a position of 0 to 20 % pitch at a position of 5 to 25 % Cax, which gently slopes from this apex toward a downstream side and the suction side surface of the adjacently disposed turbine stationary blade or turbine moving blade, and which slopes slightly steeply from the apex toward an upstream side, is provided between one turbine stationary blade or turbine moving blade and another turbine stationary blade or turbine moving blade disposed adjacent to one turbine stationary blade or turbine moving blade.
  • With the turbine blade cascade endwall according to the first aspect of the present invention, because the static pressure near the convex portion can be reduced and the flow of working fluid in the axial direction can be increased, it is possible to reduce the crossflow and to reduce secondary-flow loss that occurs in association with the crossflow; therefore, enhanced turbine performance can be achieved.
  • A turbine blade cascade endwall according to a first aspect of the present invention is a turbine blade cascade endwall that is positioned on a tip side or a hub side of a plurality of turbine stationary blades or turbine moving blades arranged in the form of a ring, wherein, defining 0% Cax as a leading edge position of the turbine stationary blades or the turbine moving blades in an axial direction and 100% Cax as a trailing edge position of the turbine stationary blades or the turbine moving blades in the axial direction, and defining 0% pitch as a position on a pressure side surface of the turbine stationary blades or the turbine moving blades and 100% pitch as a position on a suction side surface of a turbine stationary blade or a turbine moving blade facing the pressure side surface of the turbine stationary blade or the turbine moving blade, a concave portion, which is gently depressed as a whole, which has a bottom point at a position of 70 to 90 % pitch in a position of 5 to 25 % Cax, which gently slopes from this bottom point toward a downstream side and the pressure side surface of the adjacently disposed turbine stationary blade or turbine moving blade, and which slopes slightly steeply from the bottom point toward an upstream side, is provided between one turbine stationary blade or turbine moving blade and another turbine stationary blade or turbine moving blade disposed adjacent to one turbine stationary blade or turbine moving blade.
  • With the turbine blade cascade endwall according to the second aspect of the present invention, because the static pressure near the concave portion can be increased and the flow of working fluid in the axial direction can be increased, it is possible to reduce the crossflow and to reduce secondary-flow loss that occurs in association with the crossflow; therefore, enhanced turbine performance can be achieved.
  • It is further preferable that a second convex portion that is gently swollen as a whole or a convex portion be provided near a throat of the turbine blade cascade endwall according to the first aspect or the second aspect described above.
  • According to the turbine blade cascade endwall as described above, because the flow rate of the working fluid passing near the throat increases, thereby reducing the static pressure thereof and alleviating a pressure gradient generated at the suction side surface of the turbine stationary blade or the turbine moving blade in a blade-height direction, vortices generated at the suction side surface of the turbine stationary blade or the turbine moving blade can be suppressed, and therefore, it is possible to reduce secondary-flow loss associated with these vortices.
  • A turbine according to a third aspect of the present invention is provided with the turbine blade cascade endwall according to the first aspect or the second aspect described above.
    With the turbine according the third aspect of the present invention, because it is equipped with a turbine blade cascade endwall that is capable of reducing the crossflow and is capable of reducing secondary-flow loss that occurs in association with the crossflow, it is possible to achieve enhanced overall turbine performance.
  • With the present invention, an advantage is afforded in that it is possible to reduce the crossflow and to reduce secondary-flow loss that occurs in association with the crossflow, and therefore, enhanced turbine performance can be achieved.
    • Brief Description of Drawings
    • [Fig. 1] Fig. 1 is a plan view of relevant portions of a turbine blade cascade endwall according to a first embodiment of the present invention.
    • [Fig. 2] Fig. 2 is a plan view of relevant portions of a turbine blade cascade endwall according to a second embodiment of the present invention.
    • [Fig. 3] Fig. 3 is a plan view of relevant portions of a turbine blade cascade endwall according to a third embodiment of the present invention.
    • [Fig. 4] Fig. 4 is a plan view of relevant portions of a turbine blade cascade endwall according to a fourth embodiment of the present invention.
    • [Fig. 5] Fig. 5 is a plan view of relevant portions of a turbine blade cascade endwall according to another embodiment of the present invention.
    • [Fig. 6] Fig. 6 is a diagram showing isobaric lines at a suction side surface of a turbine stationary blade shown in Fig. 5.
    Best Mode for Carrying Out the Invention
  • A first embodiment of a turbine blade cascade endwall according to the present invention will be described below, with reference to Fig. 1.
    As shown in Fig. 1, each turbine blade cascade endwall (hereinafter, referred to as "third-stage stationary-blade tip endwall) 10 according to this embodiment has a first convex portion 11 between one turbine third-stage stationary blade (hereinafter, referred to as "third-stage stationary blade") B1 and another third-stage stationary blade B1 disposed adjacent to this third-stage stationary blade B1.
    Note that, solid lines drawn on the third-stage stationary-blade tip endwall 10 in Fig. 1 indicate contour lines of the first convex portion 11, contour lines of a second convex portion 12, to be described later, and contour lines of a third convex portion 13, to be described later.
  • The first convex portion 11 has an apex (peak) P1 at a position of 0 to 20 % pitch (substantially 7 % pitch in this embodiment) at a position of 5 to 25 % Cax (substantially 14 % Cax in this embodiment) and is, as a whole, a gently (smoothly) swollen portion which moderately slopes, from the apex P1, toward the downstream side and the suction side surface of the adjacently disposed third-stage stationary blade B1, and which slopes slightly steeply (slopes at a sloping angle that is larger (steeper) than a sloping angle toward the downstream side and the suction side surface of the adjacently disposed third-stage stationary blade B1 from the apex P1) toward the upstream side from the apex P1.
    Here, 0 % Cax indicates a leading edge position of the third-stage stationary blade B1 in the axial direction, and 100 % Cax indicates a trailing edge position of the third-stage stationary blade B1 in the axial direction. - (minus) indicates a position on the upstream side going up from the leading edge position of the third-stage stationary blade B1 in the axial direction, and + (plus) indicates a position on the downstream side going down from the leading edge position of the third-stage stationary blade B1 in the axial direction. Furthermore, 0 % pitch indicates a position on the pressure side surface of the third-stage stationary blade B1, and 100 % pitch indicates a position on the suction side surface of the third-stage stationary blade B1.
    The height (degree of convexity) of the apex P1 of this first convex portion 11 is set at 5 % to 20 % (about 13 % in this embodiment) of the axial chord length of the third-stage stationary blade B1 (length of the third-stage stationary blade B1 in the axial direction).
  • Note that, as shown in Fig. 1, the third-stage stationary-blade tip endwall 10 according to this embodiment has, in addition to the first convex portion 11, a second convex portion 12 that moderately slopes toward a base of the first convex portion 11 from a position of substantially 100 % pitch at a position of substantially 0 % Cax, and a third convex portion 13 that moderately slopes toward the base of the first convex portion 11 from a position of substantially 100 % pitch at a position of substantially 90 % Cax.
  • With the third-stage stationary-blade tip endwall 10 according to this embodiment, because the static pressure near the first convex portion 11 can be reduced and the flow of working fluid in the axial direction can be increased, it is possible to reduce cross flow and to reduce secondary-flow loss that occurs in association with the crossflow; therefore, enhanced turbine performance can be achieved.
  • A second embodiment of a turbine blade cascade endwall according to the present invention will be described with reference to Fig. 2.
    As shown in Fig. 2, each turbine blade cascade endwall (hereinafter, referred to as "third-stage stationary-blade hub endwall) 20 according to this embodiment has a fourth convex portion 21 between one turbine third-stage stationary blade (hereinafter, referred to as "third-stage stationary blade") B1 and another third-stage stationary blade B1 disposed adjacent to this third-stage stationary blade B1. Note that, solid lines drawn on the third-stage stationary-blade hub endwall 20 in Fig. 2 indicate contour lines of the fourth convex portion 21 and contour lines of a fifth convex portion 22, to be described later.
  • The fourth convex portion 21 has an apex (peak) P2 at a position of 0 to 20 % pitch (substantially 3 % pitch in this embodiment) at a position of 5 to 25 % Cax (substantially 14 % Cax in this embodiment) and is, as a whole, a gently (smoothly) swollen portion which moderately slopes from the apex P2 toward the downstream side and the suction side surface of the adjacently disposed third-stage stationary blade B1, and which slopes slightly steeply (slopes at a sloping angle that is larger (steeper) than a sloping angle toward the downstream side and the suction side surface of the adjacently disposed third-stage stationary blade B1 from the apex P2) toward the upstream side from the apex P2.
    The height (degree of convexity) of the apex P2 of this fourth convex portion 21 is set at 5 % to 20 % (about 12.5 % in this embodiment) of the axial chord length of the third-stage stationary blade B1 (length of the third-stage stationary blade B1 in the axial direction).
  • Note that, as shown in Fig. 2, the third-stage stationary-blade hub endwall 20 according to this embodiment has the fifth convex portion 22 that moderately slopes toward a base of the fourth convex portion 21 from a suction side surface located between substantially -10 % Cax and substantially 85 % Cax of the adjacently disposed third-stage stationary blade B1.
  • With the third-stage stationary-blade hub endwall 20 according to this embodiment, because the static pressure near the fourth convex portion 21 can be reduced and the flow of working fluid in the axial direction can be increased, it is possible to reduce crossflow and to reduce secondary-flow loss that occurs in association with the crossflow; therefore, enhanced turbine performance can be achieved.
  • A third embodiment of a turbine blade cascade endwall according to the present invention will be described with reference to Fig. 3.
    As shown in Fig. 3, each turbine blade cascade endwall (hereinafter, referred to as "fourth-stage stationary-blade tip endwall) 30 according to this embodiment has a first concave portion 31 between one turbine fourth-stage turbine stationary blade (hereinafter, referred to as "fourth-stage stationary blade") B2 and another fourth-stage stationary blade B2 disposed adjacent to this fourth-stage stationary blade B2. Note that, solid lines drawn on the fourth-stage stationary-blade tip endwall 30 in Fig. 3 indicate isobathic lines of the first concave portion 31 and isobathic lines of a sixth convex portion 32, to be described later.
  • The first concave portion 31 has a bottom point (depression peak) P3 at a position of 70 to 90 % pitch (substantially 83 % pitch in this embodiment) at a position of 5 to 25 % Cax (substantially 17 % Cax in this embodiment) and is, as a whole, a gently (smoothly) depressed portion which moderately slopes from the bottom point P3 toward the downstream side and the pressure side surface of the adjacently disposed fourth-stage stationary blade B2, and which slopes slightly steeply (slopes at a sloping angle that is larger (steeper) than a sloping angle toward the downstream side and the pressure side surface of the adjacently disposed fourth-stage stationary blade B2 from the bottom point P3) toward the upstream side from the bottom point P3.
    The depth (degree of concavity) of the bottom point P3 of this first concave portion 31 is set at 5 % to 15 % (about 6 % in this embodiment) of the axial chord length of the fourth-stage stationary blade B2 (length of the fourth-stage stationary blade B2 in the axial direction).
  • Note that, as shown in Fig. 3, the fourth-stage stationary-blade tip endwall 30 according to this embodiment has a sixth convex portion 32 that has an apex (peak) P4 at a position of substantially 90 % pitch at a position of substantially 90 % Cax and that moderately slopes toward the bottom point P3 and a pressure side surface of the adjacently disposed fourth-stage stationary blade B2.
  • With the fourth-stage stationary-blade tip endwall 30 according to this embodiment, because the static pressure near the first concave portion 31 can be increased and the flow of working fluid in the axial direction can be increased, it is possible to reduce crossflow and to reduce secondary-flow loss that occurs in association with the crossflow; therefore, enhanced turbine performance can be achieved.
  • A fourth embodiment of a turbine blade cascade endwall according to the present invention will be described with reference to Fig. 4.
    As shown in Fig. 4, each turbine blade cascade endwall (hereinafter, referred to as "fourth-stage stationary-blade hub endwall) 40 according to this embodiment has a second concave portion 41 between one turbine fourth-stage stationary blade (hereinafter, referred to as "fourth-stage stationary blade") B2 and another fourth-stage stationary blade B2 disposed adjacent to this fourth-stage stationary blade B2. Note that, solid lines drawn on the fourth-stage stationary-blade hub endwall 40 in Fig. 4 indicate isobathic lines of the second concave portion 41.
  • The second concave portion 41 has a bottom point (depression peak) P5 at a position of 70 to 90 % pitch (substantially 81 % pitch in this embodiment) at a position of 5 to 25 % Cax (substantially 18 % Cax in this embodiment) and is, as a whole, a gently (smoothly) depressed portion which moderately slopes from the bottom point P5 toward the downstream side and the pressure side surface of the adjacently disposed fourth-stage stationary blade B2, and which slopes slightly steeply (slopes at a sloping angle that is larger (steeper) than a sloping angle toward the downstream side and the pressure side surface of the adjacently disposed fourth-stage stationary blade B2 from the bottom point P5) toward the upstream side from the bottom point P5.
    The depth (degree of concavity) of the bottom point P5 of this second concave portion 41 is set at 5 % to 15 % (about 9.4 % in this embodiment) of the axial chord length of the fourth-stage stationary blade B2 (length of the fourth-stage stationary blade B2 in the axial direction).
  • With the fourth-stage stationary-blade hub endwall 40 according to this embodiment, because the static pressure near the second concave portion 41 can be increased and the flow of working fluid in the axial direction can be increased, it is possible to reduce crossflow and to reduce secondary-flow loss that occurs in association with the crossflow; therefore, enhanced turbine performance can be achieved.
  • With a turbine equipped with the turbine blade cascade endwall 10, 20, 30, or 40 according to the embodiments described above, because it is equipped with the turbine blade cascade endwall 10, 20, 30, or 40 that is capable of reducing crossflow and is capable of reducing secondary-flow loss that occurs in association with the crossflow, it is possible to achieve enhanced overall turbine performance.
  • As shown in Fig. 5, in the above-described embodiments, it is further preferable that a seventh convex portion 51 (not shown) be provided (formed) on the turbine blade cascade endwall 10, 20 , 30, or 40 near a throat thereof.
    By providing such a seventh convex portion 51 on the turbine blade cascade endwall 10, 20, 30, or 40 near the throat thereof, because the flow rate of working fluid passing near the throat increases, thereby reducing the static pressure thereof and alleviating a pressure gradient generated at the suction side surfaces of the third-stage stationary blade B1 and the fourth-stage stationary blade B2 in a blade-height direction (up-down direction in Fig. 6), as in the contour lines shown by the solid lines in the blade surface in Fig. 6, vortices generated at the suction side surfaces of the third-stage stationary blade B1 and the fourth-stage stationary blade B2 can be suppressed, and therefore, it is possible to reduce secondary-flow loss associated with these vortices.
  • The present invention is not limited to the above-described embodiments, and appropriate modifications, alterations, and combinations thereof that do not depart from the gist of the present invention are possible.
  • In the above-described embodiments, a turbine blade cascade endwall has been described as exemplified in the third-stage stationary-blade tip endwall, the third-stage stationary-blade hub endwall, the fourth-stage stationary-blade tip endwall, and the fourth-stage stationary-blade hub endwall; however, the present invention is not limited thereto, and it can be applied to a hub endwall of turbine moving blades, a tip endwall of turbine moving blades, a stationary-blade tip endwall of other stages, or a stationary-blade tip endwall of other stages.
  • Furthermore, the turbine blade cascade endwall according to the present invention can be applied to both a gas turbine and a steam turbine.

Claims (4)

  1. A turbine blade cascade endwall that is positioned on a tip side or a hub side of a plurality of turbine stationary blades or turbine moving blades arranged in the form of a ring, wherein,
    defining 0% Cax as a leading edge position of the turbine stationary blades or the turbine moving blades in an axial direction and 100% Cax as a trailing edge position of the turbine stationary blades or the turbine moving blades in the axial direction, and defining 0% pitch as a position on a pressure side surface of the turbine stationary blades or the turbine moving blades and 100% pitch as a position on a suction side surface of a turbine stationary blade or a turbine moving blade facing the pressure side surface of the turbine stationary blade or the turbine moving blade,
    a convex portion that is gently swollen as a whole, that has an apex at a position of 0 to 20 % pitch at a position of 5 to 25 % Cax, that gently slopes from this apex toward a downstream side and the suction side surface of the adjacently disposed turbine stationary blade or turbine moving blade, and that slopes slightly steeply from the apex toward an upstream side is provided between one turbine stationary blade or turbine moving blade and another turbine stationary blade or turbine moving blade disposed adjacent to one turbine stationary blade or turbine moving blade.
  2. A turbine blade cascade endwall that is positioned on a tip side or a hub side of a plurality of turbine stationary blades or turbine moving blades arranged in the form of a ring, wherein,
    defining 0% Cax as a leading edge position of the turbine stationary blades or the turbine moving blades in an axial direction and 100% Cax as a trailing edge position of the turbine stationary blades or the turbine moving blades in the axial direction, and defining 0% pitch as a position on a pressure side surface of the turbine stationary blades or the turbine moving blades and 100% pitch as a position on a suction side surface of a turbine stationary blade or a turbine moving blade facing the pressure side surface of the turbine stationary blade or the turbine moving blade,
    a concave portion that is gently depressed as a whole, that has a bottom point at a position of 70 to 90 % pitch in a position of 5 to 25 % Cax, that gently slopes from this bottom point toward a downstream side and the pressure side surface of the adjacently disposed turbine stationary blade or turbine moving blade, and that slopes slightly steeply from the bottom point toward an upstream side is provided between one turbine stationary blade or turbine moving blade and another turbine stationary blade or turbine moving blade disposed adjacent to one turbine stationary blade or turbine moving blade.
  3. A turbine blade cascade endwall according to Claim 1 or 2, wherein a second convex portion that is gently swollen as a whole or a convex portion is provided near a throat.
  4. A turbine provided with a turbine blade cascade endwall according to any one of Claims 1 to 3.
EP08872470.3A 2008-02-12 2008-09-25 Turbine blade-cascade end wall Active EP2241723B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
JP2008030937A JP5291355B2 (en) 2008-02-12 2008-02-12 Turbine cascade endwall
PCT/JP2008/067231 WO2009101722A1 (en) 2008-02-12 2008-09-25 Turbine blade-cascade end wall

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EP2241723A1 true EP2241723A1 (en) 2010-10-20
EP2241723A4 EP2241723A4 (en) 2013-03-06
EP2241723B1 EP2241723B1 (en) 2014-08-13

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US (1) US20100284818A1 (en)
EP (1) EP2241723B1 (en)
JP (1) JP5291355B2 (en)
KR (1) KR20100097757A (en)
CN (1) CN101925723B (en)
WO (1) WO2009101722A1 (en)

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EP3404211A1 (en) * 2017-05-15 2018-11-21 MTU Aero Engines GmbH Blade cascade segment for a turbine with contoured platform surface, corresponding blade cascade, blade channel, platform, turbine and aircraft engine
EP3404210A1 (en) * 2017-05-15 2018-11-21 MTU Aero Engines GmbH Blade cascade segment for a turbomachine with non-axisymmetric platform surface, corresponding blade cascade, blade channel, platform, and turbomachine

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Publication number Priority date Publication date Assignee Title
US8403645B2 (en) 2009-09-16 2013-03-26 United Technologies Corporation Turbofan flow path trenches
FR2950942B1 (en) * 2009-10-02 2013-08-02 Snecma ROTOR OF A TURBOMACHINE COMPRESSOR WITH OPTIMIZED INTERNAL END WALL
JP2012233406A (en) 2011-04-28 2012-11-29 Hitachi Ltd Gas turbine stator vane
JP5842382B2 (en) 2011-05-13 2016-01-13 株式会社Ihi Gas turbine engine
US8915706B2 (en) 2011-10-18 2014-12-23 General Electric Company Transition nozzle
US9051843B2 (en) 2011-10-28 2015-06-09 General Electric Company Turbomachine blade including a squeeler pocket
US8992179B2 (en) * 2011-10-28 2015-03-31 General Electric Company Turbine of a turbomachine
US9255480B2 (en) 2011-10-28 2016-02-09 General Electric Company Turbine of a turbomachine
US8967959B2 (en) 2011-10-28 2015-03-03 General Electric Company Turbine of a turbomachine
CN102536329B (en) * 2011-12-31 2014-04-02 西北工业大学 Modeling method for axis-asymmetric end wall of annular blade grid of air compressor or turbine
US9103213B2 (en) 2012-02-29 2015-08-11 General Electric Company Scalloped surface turbine stage with purge trough
US9085985B2 (en) 2012-03-23 2015-07-21 General Electric Company Scalloped surface turbine stage
US9267386B2 (en) 2012-06-29 2016-02-23 United Technologies Corporation Fairing assembly
EP2696029B1 (en) * 2012-08-09 2015-10-07 MTU Aero Engines AG Blade row with side wall contours and fluid flow engine
US10344601B2 (en) 2012-08-17 2019-07-09 United Technologies Corporation Contoured flowpath surface
CN106089806A (en) * 2016-05-30 2016-11-09 西北工业大学 A kind of diffuser that reduces separates the end wall processing method of loss
DE102016211315A1 (en) 2016-06-23 2017-12-28 MTU Aero Engines AG Runner or vane with raised areas
EP3369892B1 (en) * 2017-03-03 2020-08-19 MTU Aero Engines GmbH Contouring of a blade row platform
CN111919013B (en) * 2018-03-30 2022-11-15 西门子能源全球两合公司 Turbine stage platform with end wall contouring incorporating wave-shaped mating surfaces
US11639666B2 (en) 2021-09-03 2023-05-02 Pratt & Whitney Canada Corp. Stator with depressions in gaspath wall adjacent leading edges
US11415012B1 (en) * 2021-09-03 2022-08-16 Pratt & Whitney Canada Corp. Tandem stator with depressions in gaspath wall
CN114542502B (en) * 2022-01-26 2023-05-26 西北工业大学 Adjustable compressor/turbine blade cascade experimental device of blade cascade front end wall vortex generator
DE102022113750A1 (en) * 2022-05-31 2023-11-30 MTU Aero Engines AG Annulus contouring

Family Cites Families (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB944166A (en) * 1960-03-02 1963-12-11 Werner Hausammann Rotor for turbines or compressors
GB9417406D0 (en) * 1994-08-30 1994-10-19 Gec Alsthom Ltd Turbine blade
DE19650656C1 (en) * 1996-12-06 1998-06-10 Mtu Muenchen Gmbh Turbo machine with transonic compressor stage
CN2288271Y (en) * 1997-05-13 1998-08-19 北京全三维动力工程有限公司 Cambered stator blade grid for tangential turbine
GB9823840D0 (en) * 1998-10-30 1998-12-23 Rolls Royce Plc Bladed ducting for turbomachinery
US6419446B1 (en) * 1999-08-05 2002-07-16 United Technologies Corporation Apparatus and method for inhibiting radial transfer of core gas flow within a core gas flow path of a gas turbine engine
US6669445B2 (en) * 2002-03-07 2003-12-30 United Technologies Corporation Endwall shape for use in turbomachinery
US6969232B2 (en) * 2002-10-23 2005-11-29 United Technologies Corporation Flow directing device
JP4346412B2 (en) * 2003-10-31 2009-10-21 株式会社東芝 Turbine cascade
US7690890B2 (en) * 2004-09-24 2010-04-06 Ishikawajima-Harima Heavy Industries Co. Ltd. Wall configuration of axial-flow machine, and gas turbine engine
EP1828543B1 (en) * 2004-12-21 2016-03-16 Honeywell International Inc. Turbine wheel with backswept inducer
US7134842B2 (en) * 2004-12-24 2006-11-14 General Electric Company Scalloped surface turbine stage
US7220100B2 (en) * 2005-04-14 2007-05-22 General Electric Company Crescentic ramp turbine stage
GB0518628D0 (en) * 2005-09-13 2005-10-19 Rolls Royce Plc Axial compressor blading
JP4616781B2 (en) * 2006-03-16 2011-01-19 三菱重工業株式会社 Turbine cascade endwall
US7887297B2 (en) * 2006-05-02 2011-02-15 United Technologies Corporation Airfoil array with an endwall protrusion and components of the array

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3404211A1 (en) * 2017-05-15 2018-11-21 MTU Aero Engines GmbH Blade cascade segment for a turbine with contoured platform surface, corresponding blade cascade, blade channel, platform, turbine and aircraft engine
EP3404210A1 (en) * 2017-05-15 2018-11-21 MTU Aero Engines GmbH Blade cascade segment for a turbomachine with non-axisymmetric platform surface, corresponding blade cascade, blade channel, platform, and turbomachine
US10934849B2 (en) 2017-05-15 2021-03-02 MTU Aero Engines AG Endwall contouring for a turbomachine

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EP2241723A4 (en) 2013-03-06
KR20100097757A (en) 2010-09-03
CN101925723B (en) 2016-06-01
CN104165070A (en) 2014-11-26
JP5291355B2 (en) 2013-09-18
CN101925723A (en) 2010-12-22
EP2241723B1 (en) 2014-08-13
US20100284818A1 (en) 2010-11-11
JP2009191656A (en) 2009-08-27

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