EP2075408A2 - Leitschaufel auf letzter Stufe des Niederdruckabschnitts einer Dampfturbine - Google Patents

Leitschaufel auf letzter Stufe des Niederdruckabschnitts einer Dampfturbine Download PDF

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Publication number
EP2075408A2
EP2075408A2 EP08173020A EP08173020A EP2075408A2 EP 2075408 A2 EP2075408 A2 EP 2075408A2 EP 08173020 A EP08173020 A EP 08173020A EP 08173020 A EP08173020 A EP 08173020A EP 2075408 A2 EP2075408 A2 EP 2075408A2
Authority
EP
European Patent Office
Prior art keywords
blade
stator blade
stator
last stage
range
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.)
Withdrawn
Application number
EP08173020A
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English (en)
French (fr)
Other versions
EP2075408A3 (de
Inventor
Nicola Camerlenghi
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.)
Ansaldo Energia SpA
Original Assignee
Ansaldo Energia SpA
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 Ansaldo Energia SpA filed Critical Ansaldo Energia SpA
Publication of EP2075408A2 publication Critical patent/EP2075408A2/de
Publication of EP2075408A3 publication Critical patent/EP2075408A3/de
Withdrawn legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • 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
    • 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
    • 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
    • F05D2200/00—Mathematical features
    • F05D2200/20—Special functions
    • 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
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/31—Application in turbines in steam turbines
    • 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
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes

Definitions

  • the present invention relates to a last stage stator blade of a steam turbine low-pressure section.
  • the design of the last stage of steam turbine low-pressure sections is particularly important. Indeed, given the large average radius of the blades and the consequent high speeds of the progressing flow, the power produced in the last stage of the low-pressure section is much higher than in the previous stages of the same section. Since the low-pressure section produces a considerable fraction of the overall power delivered by the turbine and, furthermore, in this section a lower number of stages than in the high and medium pressure sections exist, the efficiency of the last stage of the low-pressure section affects the overall efficiency of the whole turbine in a non-negligible manner.
  • the efficiency of the existing last stage stator blades is not adequate for processing the supersonic flow normally present between the blade base and the three-quarters of the blade height.
  • the blade height portions having the highest efficiency i.e. the most remote stator blade portion from the turbine axis and the closest rotor blade portion
  • the flow is not adequately moved between the stator portion and the rotor portion of the last stage.
  • the overall efficiency of the turbines is thus strongly limited by the low efficiency of the last stage of the low-pressure section.
  • a last stage stator blade of a steam turbine low-pressure section is provided as claimed in claim 1.
  • reference numeral 1 indicates a low-pressure section of a steam turbine.
  • the low-pressure section 1 comprises a shaft 2, extending along a machine axis A, and a plurality of intermediate stages 3 and an outlet stage or last stage 5, all accommodated inside a casing 4.
  • the intermediate stages 3 and the last stage 5 are arranged in sequence along the machine axis A according to a flow direction D of the steam.
  • Each intermediate stage 3 comprises a respective array of rotor blades 6 and a respective array of stator blades 7, facing each other.
  • the rotor blades 6 radially extend from the shaft 2, to which they are fixed.
  • the stator blades 7 of each array also radially oriented, are fixed to the casing 4 by respective anchoring devices 8.
  • the radially internal ends of the stator blades 7 of each array are provided with a roof.
  • the last stage 5 comprises an array of rotor blades 12, radially arranged and fixed to the shaft 2, and an array of stator blades 13, placed upstream of the rotor blades 12 according to the flow direction D of the steam (see enlargement in figure 2 ).
  • the height of rotor blades 12 is in the range between 88.9 cm (35") and 101.6 cm (40"), e.g. 93.98 cm (37").
  • stator blades 13 are fixed to the casing 4 by means of anchoring devices 14, extend in the radial direction and have internal ends provided with roofs 15.
  • stator blades 13 of the last stage 5 is shown more in detail in figures 3-8 .
  • the stator blade 13 has a curvilinear leading edge 13a and a curvilinear trailing edge 13b and has a blade height H T , defined by the difference between a maximum radial coordinate, according to a radial reference axis Z, of a peripheral portion or "tip" 13c, and a minimum radial coordinate of a base or "hub” portion 13d.
  • the blade height H T is in the range between 71 cm and 75 cm.
  • blade sections will refer to cylindrical sections obtained by the intersection of the stator blade 13 with cylindrical surfaces having the machine axis A as axis and a given radius.
  • section radius R S of a blade section S means the radius of the cylindrical surface which generates the blade section S, i.e. the distance of the blade section S from the machine axis A according to a direction defined by the radial reference axis Z.
  • the stator blade 13 has blade sections S with respective section radii R S , radially stacked and joined according to stacking lines (specifically, in figures 4 and 5 , the blade sections S 1 , S 2 , ..., S K , are shown with the respective section radii R S1 , R S2 , ..., R SK ). More specifically, the blade sections S 1 , S 2 , ..., S K are stacked according to a tangential stacking line LEAN and to an axial stacking line SWEEP ( figures 4 and 5 ).
  • the blade sections S 1 , S 2 , ..., S K are axially (according to a direction defined by a central reference axis X coinciding with the machine axis A of the turbine) and tangentially (according to a direction defined by a tangential reference axis R ⁇ , perpendicular to axis X and axis Z) translated with respect to a peripheral vertex V P of the trailing edge 13b of the stator blade 13.
  • each blade section S 1 , S 2 , ..., S K is determined by the interpolation of the tangential stacking line LEAN and the axial stacking line SWEEP ( figures 4 and 5 ), respectively, at the respective section radius R S1 , R S2 , ..., R SK .
  • the tangential stacking line LEAN defines an orthogonal projection of the trailing edge 13b of the stator blade 13 on a plane (R, R ⁇ ) perpendicular to the machine axis A and identified by radial reference axis Z and tangential reference axis R ⁇ ( figure 4 ).
  • the tangential stacking line LEAN is a fourth-order Bezier curve having a concavity towards a pressure side or belly 13e of the stator blade 13.
  • the tangential stacking line LEAN is defined by four check points, as shown in figure 6 , where Z indicates the radial reference axis and R ⁇ the tangential reference axis, perpendicular to the radial reference axis Z.
  • a first check point 17 and a second check point 18 define one end at the periphery (at the tip) and one end at the base (at the hub) of the tangential stacking line LEAN, respectively.
  • a third check point 19 and a fourth check point 20 define the concavity of the tangential stacking line LEAN.
  • the tangential stacking line LEAN has a tangent angle ⁇ T at the periphery or tip, defined by a direction parallel to the radial reference axis Z in the first check point 17 and by the line joining the first and third check points 17, 19; and a tangent angle ⁇ H at the base or at the hub, defined by a direction parallel to the radial reference axis Z in the second check point 18 and by the line joining the second and the fourth check points 18, 20.
  • the concavity of the tangential stacking line LEAN is further determined by an influence range at the base or at the hub A H and by an influence range at the periphery or at the tip A T , given by the distance between the first and the third check points 17, 19 and by the distance between the second and the fourth check points 18, 20, respectively, in the direction of the radial reference axis Z.
  • the influence range at the hub A H and the influence range at the tip A T are normalized as compared to the blade height H T , are non-dimensional and vary between 0 and 0.5.
  • the tangential stacking line LEAN is defined by values of the tangent angle at the base ⁇ H in the range between 0° and 20°; by values of the tangent angle at the periphery ⁇ T in the range between 10° and 20°; by values of the influence range at the axis A H in the range between 0.05 and 0.15; and by values of the influence range at the periphery A T in the range between 0.15 and 0.25.
  • the angle at the axis ( ⁇ H ) is 18°; the angle at the periphery ( ⁇ T ) is 15°; the influence range at the axis (H H ) is 0.1; and the influence range at the periphery (H T ) is 0.22938.
  • the axial stacking line SWEEP defines a projection of the trailing edge 13b of the stator blade 13 on a meridian plane P M , targeted by central reference axis X and radial reference axis Z, and passing through the peripheral vertex V P of the trailing edge 13b ( figures 5 and 7 ).
  • the axial stacking line SWEEP is defined by a rectilinear segment and, for a second length 22 towards the tip portion 13d, by a fourth-order Bezier curve, joined to the rectilinear segment and tangential to the rectilinear segment itself at the joining point J.
  • the first length 21 and the second length 22 each preferably extend for approximately half of the blade height H T .
  • the peripheral portion 13c of the stator blade 13 is inclined with respect to the machine axis A so as to comply with the profile of the median channel of the turbine, which preferably has a taper ratio lower than 47°.
  • the blade sections S 1 , S 2 , ..., S K have profiles 24a-24d such as to define converging-diverging blade-to-blade channels 25 between pairs of adjacent stator blades 13, as shown in figure 8 which represents a development on a blade-to-blade plane (i.e. on a plane obtained by developing a cylindrical intersection surface centered about the machine axis A and intersecting the stator blades 13). More in detail, on the pressure side of the stator blade 13, the profiles of the blade sections S 1 , S 2 , ..., S K are defined by a fourth-order Bezier curve for an inlet part 24a, and by a first rectilinear segment, for an outlet part 24b.
  • the profiles of the blade sections S 1 , S 2 , ..., S K are defined by a fourth-order Bezier curve for an inlet part 24c, and by a second rectilinear segment for an outlet part 24d.
  • stator blades 13 as those described allows to considerably improve the efficiency of the last stage 5.
  • joining the blade sections as described allows to reduce the Mach number where it is higher and thus more critical for the efficiency, i.e. at the outlet from the stator array at the lower part (at the base) of the blade.
  • the Mach number slightly increases at the periphery of the stator blade. But in this region, the Mach number value is however considerably lower than at the base and does not significantly affect the efficiency. In general, the effect of the Mach number reduction at the base of the stator blade 13 prevails and the efficiency of the last stage is higher.
  • the steam flow is optimally distributed to the meridian channel.
  • the specific flow rate is modified so as to greatly exploit the meridian channel part having the highest efficiency, both in the stator portion (i.e. towards the periphery) and the rotor portion (close to the shaft).
  • the shape of the stator blade 13 thus produces beneficial effects even on the array of the rotor blades 12 of the last stage 5, although without interventions on the structure thereof. The efficiency of the last stage is thus further increased.
  • the degree of reaction of the last stage 5 is reduced over 70% of the blade height H T , while it is higher in the remaining portion.
  • the enthalpy difference used by the array of stator blades 13 is higher at the periphery (where the Mach number is lower and thus the efficiency is higher) and lower at the base.
  • stator blade 13 also has beneficial effects on the array of rotor blades 12 of the last stage 5.
  • the flow exiting from the array of stator blades 13 is such that the Mach number related to the inlet of the array of rotor blades 12 increases at the base (where it is lower) and decreases at the periphery (where it is very high).
  • the effect related to the Mach number reduction in the regions where it is higher considerably prevails and is translated into an increase of the efficiency of the last stage 5 (at the top of the rotor blades 12 of the last stage 5 the flow is strongly transonic).

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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)
EP08173020A 2007-12-28 2008-12-29 Leitschaufel auf letzter Stufe des Niederdruckabschnitts einer Dampfturbine Withdrawn EP2075408A3 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
ITMI20072441 ITMI20072441A1 (it) 2007-12-28 2007-12-28 Pala statorica di ultimo stadio di sezione di bassa pressione di una turbina a vapore

Publications (2)

Publication Number Publication Date
EP2075408A2 true EP2075408A2 (de) 2009-07-01
EP2075408A3 EP2075408A3 (de) 2013-03-06

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EP (1) EP2075408A3 (de)
IT (1) ITMI20072441A1 (de)

Cited By (33)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2412922A1 (de) * 2010-07-30 2012-02-01 Alstom Technology Ltd Niederdruckdampfturbine und Verfahren zu deren Betrieb
US8137062B2 (en) 2010-05-11 2012-03-20 General Electric Company Turbomachine nozzle
EP2434094A2 (de) 2010-09-28 2012-03-28 Hitachi Ltd. Leitschaufel für Dampfturbine und Dampfturbine
KR101322554B1 (ko) * 2012-03-27 2013-10-28 가부시키가이샤 히타치세이사쿠쇼 증기 터빈의 고정익 및 그것을 사용한 증기 터빈
CN103541774A (zh) * 2013-11-14 2014-01-29 上海汽轮机厂有限公司 涡轮叶片设计方法
JP2014139431A (ja) * 2012-12-13 2014-07-31 Nuovo Pignone Srl 形状付けされたチャネルを備えたターボ機械ブレードを積層造形によって製造する方法、ターボ機械ブレード、およびターボ機械
EP3108112A4 (de) * 2014-02-19 2017-02-22 United Technologies Corporation Gasturbinenmotor-tragfläche
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US10184483B2 (en) 2014-02-19 2019-01-22 United Technologies Corporation Gas turbine engine airfoil
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DE59709447D1 (de) * 1997-11-17 2003-04-10 Alstom Switzerland Ltd Endstufe für axialdurchströmte Turbine
US6709239B2 (en) * 2001-06-27 2004-03-23 Bharat Heavy Electricals Ltd. Three dimensional blade
DE602005011683D1 (de) * 2005-07-19 2009-01-22 Honeywell Int Inc Turbolader mit variabler düse
WO2007113149A1 (de) * 2006-03-31 2007-10-11 Alstom Technology Ltd Leitschaufel für eine strömungsmaschine, insbesondere für eine dampfturbine

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US8137062B2 (en) 2010-05-11 2012-03-20 General Electric Company Turbomachine nozzle
EP2412922A1 (de) * 2010-07-30 2012-02-01 Alstom Technology Ltd Niederdruckdampfturbine und Verfahren zu deren Betrieb
JP2012031864A (ja) * 2010-07-30 2012-02-16 Alstom Technology Ltd 低圧蒸気タービン及び低圧蒸気タービンを運転する方法
EP2434094A2 (de) 2010-09-28 2012-03-28 Hitachi Ltd. Leitschaufel für Dampfturbine und Dampfturbine
US9011084B2 (en) 2010-09-28 2015-04-21 Mitsubishi Hitachi Power Systems, Ltd. Steam turbine stator vane and steam turbine using the same
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JP2014139431A (ja) * 2012-12-13 2014-07-31 Nuovo Pignone Srl 形状付けされたチャネルを備えたターボ機械ブレードを積層造形によって製造する方法、ターボ機械ブレード、およびターボ機械
CN103541774A (zh) * 2013-11-14 2014-01-29 上海汽轮机厂有限公司 涡轮叶片设计方法
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EP3404212A1 (de) * 2017-05-16 2018-11-21 Rolls-Royce plc Kompressorschaufelelement
AU2019282972B2 (en) * 2018-06-08 2022-09-01 Global Energy Co., Ltd. Horizontal axis rotor
US12135007B2 (en) 2018-06-08 2024-11-05 Global Energy Co., Ltd. Horizontal shaft rotor
CN113250755A (zh) * 2021-04-15 2021-08-13 西北工业大学 基于非均匀有理b样条曲线的叶型的设计方法及叶片
EP4227489A1 (de) * 2022-02-11 2023-08-16 MTU Aero Engines AG Leitschaufel für eine strömungsmaschine
US12140041B2 (en) 2022-02-11 2024-11-12 MTU Aero Engines AG Stator vane for a turbomachine

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Publication number Publication date
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ITMI20072441A1 (it) 2009-06-29

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