EP2241723B1 - Turbine blade-cascade end wall - Google Patents

Turbine blade-cascade end wall Download PDF

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Publication number
EP2241723B1
EP2241723B1 EP08872470.3A EP08872470A EP2241723B1 EP 2241723 B1 EP2241723 B1 EP 2241723B1 EP 08872470 A EP08872470 A EP 08872470A EP 2241723 B1 EP2241723 B1 EP 2241723B1
Authority
EP
European Patent Office
Prior art keywords
turbine
turbine blade
blade
endwall
stage
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.)
Active
Application number
EP08872470.3A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP2241723A4 (en
EP2241723A1 (en
Inventor
Yasuro Sakamoto
Eisaku Ito
Susumu Wakazono
Takashi Hiyama
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 Power Ltd
Original Assignee
Mitsubishi Hitachi Power Systems Ltd
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 Mitsubishi Hitachi Power Systems Ltd filed Critical Mitsubishi Hitachi Power Systems Ltd
Publication of EP2241723A1 publication Critical patent/EP2241723A1/en
Publication of EP2241723A4 publication Critical patent/EP2241723A4/en
Application granted granted Critical
Publication of EP2241723B1 publication Critical patent/EP2241723B1/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • 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 relates to a turbine blade cascade endwall according to the preamble portion of claim 1 or 2.
  • crossflow secondary flow
  • Patent Citation 1 U.S. Patent No. 6,283,713 , Specification.
  • 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.
  • 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.
  • EP 1681438 A2 discloses a turbine blade cascade end wall of a turbine blade stage which is provided with a convex portion having its peak at about 0 to 5% Cax and at a pitch of about 95 to 100%, and a concave or depression portion having its bottom point at about 50% Cax and 0% pitch.
  • US 2007/258819 A1 discloses a turbine blade cascade end wall of a turbine blade stage which has a concave portion with a bottom point at approximately 30 to about 120% of the axial cord length of the blade, and a lateral range from a pressure surface of the blade to about 60% of the passage width.
  • the concave portion is thus rather located towards the downstream end in the axial direction of the cascade end wall.
  • the present invention employs a turbine blade cascade end wall as defined by claim 1 or by claim 2.
  • the turbine blade cascade end wall has 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.
  • a turbine blade cascade endwall according to a second aspect of the present invention has 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.
  • 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.
  • 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.
  • 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.
  • a first embodiment of a turbine blade cascade endwall according to the present invention will be described below, with reference to Fig. 1 .
  • each turbine blade cascade endwall (hereinafter, referred to as "third-stage stationary-blade tip endwall) 10 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.
  • 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.
  • 0 % Cax indicates a leading edge position of the third-stage stationary blade B1 in the axial direction
  • 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
  • + (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.
  • 0 % pitch indicates a position on the pressure side surface of the third-stage stationary blade B1
  • 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).
  • the third-stage stationary-blade tip endwall 10 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.
  • 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.
  • FIG. 2 A second embodiment of a turbine blade cascade endwall according to the present invention will be described with reference to Fig. 2 .
  • each turbine blade cascade endwall (hereinafter, referred to as "third-stage stationary-blade hub endwall) 20 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.
  • 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).
  • the third-stage stationary-blade hub endwall 20 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.
  • a third embodiment of a turbine blade cascade endwall according to the present invention will be described with reference to Fig. 3 .
  • each turbine blade cascade endwall (hereinafter, referred to as "fourth-stage stationary-blade tip endwall) 30 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.
  • solid lines drawn on the fourth-stage stationary-blade tip endwall 30 in Fig. 3 indicate contour lines of the first concave portion 31 and contour 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).
  • the fourth-stage stationary-blade tip endwall 30 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.
  • the fourth-stage stationary-blade tip endwall 30 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 .
  • each turbine blade cascade endwall (hereinafter, referred to as "fourth-stage stationary-blade hub endwall) 40 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.
  • 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).
  • 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.
  • 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 hub endwall of other stages.
  • turbine blade cascade endwall according to the present invention can be applied to both a gas turbine and a steam turbine.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Hydraulic Turbines (AREA)
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 (ja) 2008-02-12 2008-02-12 タービン翼列エンドウォール
PCT/JP2008/067231 WO2009101722A1 (ja) 2008-02-12 2008-09-25 タービン翼列エンドウォール

Publications (3)

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

Family

ID=40956766

Family Applications (1)

Application Number Title Priority Date Filing Date
EP08872470.3A Active EP2241723B1 (en) 2008-02-12 2008-09-25 Turbine blade-cascade end wall

Country Status (6)

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

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Also Published As

Publication number Publication date
JP2009191656A (ja) 2009-08-27
US20100284818A1 (en) 2010-11-11
CN101925723B (zh) 2016-06-01
CN101925723A (zh) 2010-12-22
JP5291355B2 (ja) 2013-09-18
WO2009101722A1 (ja) 2009-08-20
CN104165070A (zh) 2014-11-26
EP2241723A4 (en) 2013-03-06
EP2241723A1 (en) 2010-10-20
KR20100097757A (ko) 2010-09-03

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