EP2738351A1 - Rotorschaufel mit einem Tränenförmig geformten Dämpfer in einer Teilhöhe des Schaufelblatts - Google Patents

Rotorschaufel mit einem Tränenförmig geformten Dämpfer in einer Teilhöhe des Schaufelblatts Download PDF

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Publication number
EP2738351A1
EP2738351A1 EP13193148.7A EP13193148A EP2738351A1 EP 2738351 A1 EP2738351 A1 EP 2738351A1 EP 13193148 A EP13193148 A EP 13193148A EP 2738351 A1 EP2738351 A1 EP 2738351A1
Authority
EP
European Patent Office
Prior art keywords
span shroud
blade
span
radially
maximum thickness
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.)
Ceased
Application number
EP13193148.7A
Other languages
English (en)
French (fr)
Inventor
Rohit Chouhan
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.)
General Electric Co
Original Assignee
General Electric Co
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 General Electric Co filed Critical General Electric Co
Publication of EP2738351A1 publication Critical patent/EP2738351A1/de
Ceased 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
    • F01D5/22—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
    • 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
    • F05D2250/70—Shape
    • F05D2250/74—Shape given by a set or table of xyz-coordinates

Definitions

  • the invention relates generally to rotating blades for use in turbomachines. More particularly, the invention relates to a rotating blades provided with part-span shrouds between adjacent blades.
  • the fluid flow path of a turbomachine such as a steam or gas turbine is generally formed by a stationary casing and a rotor.
  • a number of stationary vanes are attached to the casing in a circumferential array, extending radially inward into the flow path.
  • a number of rotating blades are attached to the rotor in a circumferential array and extending radially outward into the flow path.
  • the stationary vanes and rotating blades are arranged in alternating rows so that a row of vanes and the immediate downstream row of blades form a "stage".
  • the vanes serve to direct the flow path so that it enters the downstream row of blades at the correct angle. Airfoils of the blades extract energy from the working fluid, thereby developing the power necessary to drive the rotor and the load attached thereto.
  • blades of the turbomachine may be subject to vibration and axial torsion as they rotate at high speeds.
  • blades typically include part-span shrouds disposed on the airfoil portions at an intermediate radial distance between the tip and the root section of each blade.
  • the part-span shrouds are typically affixed to each of the pressure (concave) and suction (convex) sides of each airfoil, such that the part-span shrouds on adjacent blades matingly engage and frictionally slide along one another during rotation of the rotor.
  • a rotatable blade for a turbomachine comprising an airfoil portion having a leading edge and a trailing edge, a radially-inner end and a radially-outer end; a root section affixed to the radially-inner end of the airfoil portion; and a substantially tear-drop shaped part-span shroud located on the airfoil portion between the root section and the radially outer end, wherein the part-span shroud is provided with cross-sectional shape having a maximum thickness located within 20 to 40% of a chord length extending from a leading edge of the part-span shroud to a trailing edge of the part-span shroud, as measured from the leading edge of the part-span shroud.
  • a turbomachine comprising a rotor rotatably mounted within a stator, the rotor including a shaft; at least one rotor wheel mounted on the shaft, each of the at least one rotor wheels including a plurality of radially outwardly extending blades mounted thereon; and wherein each blade includes an airfoil portion having a leading edge and a trailing edge, a radially-inner end and a radially-outer end, a pressure side and a suction side; a root section at the radially-inner end of the airfoil portion; and a part-span shroud located on the airfoil portion between the root section and the radially outer end, on the pressure side and the suction side, wherein the part-span shroud is provided with a substantially tear-drop cross-sectional shape having a maximum thickness located within 20 to 40% of a chord length extending between a leading edge of the part-span shroud and
  • a turbomachine comprising a rotor rotatably mounted within a stator, the rotor including a shaft; at least one rotor wheel mounted on the shaft, each of the at least one rotor wheels including a plurality of radially outwardly extending blades mounted thereon; and wherein each blade includes an airfoil portion having a leading edge and a trailing edge, a radially-inner end and a radially-outer end, a pressure side and a suction side; a root section at the radially-inner end of the airfoil portion; and a part-span shroud located on the airfoil portion between the root section and the radially outer end, on the pressure side and the suction side, wherein the part-span shroud is provided with a tear-drop cross-sectional shape having a maximum thickness located at 31%-37% of a chord length extending between a leading edge of the part-span shroud and a
  • FIG. 1 shows a perspective partial cut-away illustration of a steam turbine 10.
  • the steam turbine 10 includes a rotor assembly 12 that includes a shaft or rotor 14 and a plurality of axially spaced rotor wheels 18.
  • a plurality of rotatable blades or buckets 20 are mechanically coupled to each rotor wheel 18. More specifically, blades 20 are arranged in rows that extend circumferentially around each rotor wheel 18.
  • a plurality of stationary vanes 22 extends circumferentially around the shaft 14 and are axially positioned between adjacent rows of blades 20. The stationary vanes 22 are secured to a surrounding stator and cooperate with the rotatable blades 20 to form one of a plurality of turbine stages and define a portion of a steam flow path through turbine 10.
  • a large steam turbine unit may actually include several turbines that are co-axially coupled to the same shaft 14. Such a unit may, for example, include a high pressure turbine coupled to an intermediate-pressure turbine, which is in turn coupled to a low pressure turbine.
  • the steam turbine 10 shown in FIG. 1 comprises five stages.
  • the five stages are referred to as L0, L1, L2, L3 and L4.
  • Stage L4 is the first stage and is the smallest (in a radial direction) of the five stages.
  • Stage L3 is the second stage and is the next stage in an axial direction.
  • Stage L2 is the third stage and is shown in the middle of the five stages.
  • Stage L1 is the fourth and next-to-last stage.
  • Stage L0 is the last stage and is the largest (in a radial direction). It is to be understood that more or fewer than five stages may be present.
  • the gas turbine 110 includes a rotor assembly 112 that includes a shaft 114 and a plurality of axially spaced rotor wheels 118.
  • a plurality of rotating blades or buckets 120 are mechanically coupled to each rotor wheel 118. More specifically, blades 120 are arranged in rows that extend circumferentially around each rotor wheel 118.
  • a plurality of stationary vanes 122 are secured to a surrounding stator and extend circumferentially around shaft 114, axially positioned between adjacent rows of blades 120.
  • turbine 110 During operation, air at atmospheric pressure is compressed by a compressor and delivered to a combustion stage. In the combustion stage (represented by combustors 124), the air leaving the compressor is heated by adding fuel to the air and burning the resulting air/fuel mixture. The gas flow resulting from combustion of fuel in the combustion stage then expands through the turbine 110, delivering some of its energy to drive the turbine 110 and produce mechanical power.
  • turbine 110 consists of one or more stages. Each stage includes a row of vanes 122 and a row of rotating blades 120 mounted on a rotor wheel 118. Vanes 122 direct incoming gas from the combustion stage onto blades 120. This drives rotation of the rotor wheel 118, and as a result, shaft 114, producing mechanical power.
  • Each blade or bucket 20 includes an airfoil portion 32.
  • a root section 34 is affixed to (or integral with) a radially-inward end of the airfoil portion 32.
  • a blade attachment member 36 projects from the root section 34.
  • blade attachment member 36 may be a dovetail, but other blade attachment member shapes and configurations are well known in the art and are also contemplated herein.
  • a radially-outer tip 38 is formed to include a leading edge 40, a trailing edge 42, a suction side 44 and a pressure side 46.
  • a part-span shroud 48 is attached at an intermediate section of the airfoil portion 32 between the root section 34 and the tip 38.
  • part-span shroud sections 50, 52 are located, respectively, on the suction side 44 and pressure side 46 of the airfoil portion 32.
  • the part-span shroud sections 50, 52 of adjacent blades 20 are designed to at least partially engage along mated Z-shaped edges 54, 56 (see FIG. 4 ) as in known part-span configurations, during operation of the turbine.
  • the part-span shroud sections are joined to the airfoil portion at fillets 58 (shown for part-span shroud sections 52 but also employed with part-span shroud sections 50).
  • the blade stiffness and damping characteristics are improved as the part-span shrouds contact each other during untwisting of the blade.
  • the plurality of blades 20 thus behave as a single, continuously coupled structure that exhibits improved stiffness and dampening characteristics when compared to a discrete and uncoupled design. Blades 20 also exhibit reduced vibratory stresses.
  • FIG. 5 illustrates another known configuration where part-span shroud sections 60, 62 on adjacent, respective blades 64, 66 are designed to engage along straight, substantially-parallel edges 68, 70.
  • FIG. 6 illustrates a known cross-sectional shape for a part-span shroud (on both the pressure and suction side of the airfoil), as shown and described, for example, in U.S. Patent 5,695,323 , and typically used with shroud configurations as shown in FIGS. 3-5 .
  • the maximum thickness of the part-span cross-section is located approximately midway along the length of a chord 72 extending between the leading and trailing edges 74, 76 of the part-span shroud 78.
  • FIG. 7 illustrates a tear-drop cross-sectional shape for a part-span shroud 80 in accordance with an exemplary but nonlimiting embodiment of the invention.
  • the maximum thickness of the cross-sectional shape has been moved forward, nearer to the leading edge 82 of the part-span shroud. More specifically, the point of maximum thickness is located in a range of 20 to 40%, and preferably about 30% of the length of a chord 84 extending between the leading and trailing edges 82, 86 respectively, of the part-span shroud 80, as measured from the leading edge 82.
  • the thickness of the part-span shroud varies in opposite directions from the location of maximum thickness.
  • the tear-drop shaped part-span shroud described above is located substantially midway along the radial length of the airfoil but could be located anywhere between about 40% and 80% of the radial height of the airfoil portion as measured from the root section of the blade.
  • the maximum thickness of the part-span shroud is located at 31% of the length of the chord 84 as measured from the leading edge 82, as shown in FIG.8 .
  • the section shape or profile is defined by X-Y Cartesian coordinates where the zero reference point in the X direction is at the center of the chord along its length dimension, and the zero reference point in the Y direction is on the chord 84.
  • the coordinates of the various points indicated on the section view are found in Table I below.
  • the maximum thickness is located at 36% of the length of the chord 84 as measured from the leading edge 82, as shown in FIG.9 .
  • the section shape or profile is defined by the with X-Y Cartesian coordinates set out in a scheme similar to FIG.8 and the coordinates of the various points indicated on the section view are found in Table II below. TABLE II Sl No.
  • the maximum thickness is located at 37% of the length of the chord 84 as measured from the leading edge 82, as shown in FIG.10 .
  • the section shape or profile is defined by the X-Y Cartesian coordinates set out in a scheme similar to FIGS.8 and 9 and the coordinates of the various points indicated on the section view are found in Table III below. TABLE III Sl No.
  • part-span shrouds described herein may be used in combination with conventional airfoil tip shrouds located at the radially-outer tips 38 ( FIGS. 3 , 4 ) of the airfoils.
  • the blade 20 and part-span shroud 80 described above may be used in a variety of turbomachine environments.
  • blades having part-span shrouds 80 as described in connection with FIG. 7 may operate in any one or more of: a front stage of a compressor, a latter stage in a gas turbine or a low pressure section blade in a steam turbine.
  • the cross-sectional shape shout at 80 is applicable to the part-span shroud configurations shown in FIGS. 3-5 but is not limited to those configurations.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP13193148.7A 2012-11-30 2013-11-15 Rotorschaufel mit einem Tränenförmig geformten Dämpfer in einer Teilhöhe des Schaufelblatts Ceased EP2738351A1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US13/691,478 US20140154081A1 (en) 2012-11-30 2012-11-30 Tear-drop shaped part-span shroud

Publications (1)

Publication Number Publication Date
EP2738351A1 true EP2738351A1 (de) 2014-06-04

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EP13193148.7A Ceased EP2738351A1 (de) 2012-11-30 2013-11-15 Rotorschaufel mit einem Tränenförmig geformten Dämpfer in einer Teilhöhe des Schaufelblatts

Country Status (4)

Country Link
US (1) US20140154081A1 (de)
EP (1) EP2738351A1 (de)
JP (1) JP2014109272A (de)
CN (1) CN103850716B (de)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3379033A1 (de) * 2017-03-20 2018-09-26 General Electric Company Systeme und verfahren zur minimierung eines einfallswinkels zwischen einer anzahl von stromlinien in einem nicht gestörten strömungsfeld durch änderung eines neigungswinkels einer sehnenlinie eines dämpfers
EP4112884A1 (de) * 2021-07-01 2023-01-04 Doosan Enerbility Co., Ltd. Schaufel für eine turbomaschine, schaufelanordnung und turbine

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN104763477B (zh) * 2015-04-13 2016-03-02 大连理工大学 一种叶轮机械动叶叶尖部分围带结构
US11339670B2 (en) 2020-10-13 2022-05-24 General Electric Company Part-span shroud configurations
JP7245215B2 (ja) * 2020-11-25 2023-03-23 三菱重工業株式会社 蒸気タービン動翼

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5257908A (en) * 1991-11-15 1993-11-02 Ortolano Ralph J Turbine lashing structure
US5695323A (en) 1996-04-19 1997-12-09 Westinghouse Electric Corporation Aerodynamically optimized mid-span snubber for combustion turbine blade
US20110158810A1 (en) * 2009-12-28 2011-06-30 Kabushiki Kaisha Toshiba Turbine rotor assembly and steam turbine
US8105038B2 (en) * 2007-06-27 2012-01-31 Kabushiki Kaisha Toshiba Steam turbine, and intermediate support structure for holding row of long moving blades therein

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1618284A (en) * 1925-05-22 1927-02-22 Westinghouse Electric & Mfg Co Turbine-blade bracing
US1747690A (en) * 1927-12-15 1930-02-18 Westinghouse Electric & Mfg Co Blade lashing
US2117107A (en) * 1935-09-28 1938-05-10 Westinghouse Electric & Mfg Co Turbine blade lashing
JPS60111001A (ja) * 1983-11-21 1985-06-17 Mitsubishi Heavy Ind Ltd タ−ビン用インテグラルスタブ翼
JP2007187053A (ja) * 2006-01-12 2007-07-26 Hitachi Ltd タービン動翼
JP4713509B2 (ja) * 2007-01-26 2011-06-29 株式会社日立製作所 タービン動翼
US8075272B2 (en) * 2008-10-14 2011-12-13 General Electric Company Steam turbine rotating blade for a low pressure section of a steam turbine engine

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5257908A (en) * 1991-11-15 1993-11-02 Ortolano Ralph J Turbine lashing structure
US5695323A (en) 1996-04-19 1997-12-09 Westinghouse Electric Corporation Aerodynamically optimized mid-span snubber for combustion turbine blade
US8105038B2 (en) * 2007-06-27 2012-01-31 Kabushiki Kaisha Toshiba Steam turbine, and intermediate support structure for holding row of long moving blades therein
US20110158810A1 (en) * 2009-12-28 2011-06-30 Kabushiki Kaisha Toshiba Turbine rotor assembly and steam turbine

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3379033A1 (de) * 2017-03-20 2018-09-26 General Electric Company Systeme und verfahren zur minimierung eines einfallswinkels zwischen einer anzahl von stromlinien in einem nicht gestörten strömungsfeld durch änderung eines neigungswinkels einer sehnenlinie eines dämpfers
EP4112884A1 (de) * 2021-07-01 2023-01-04 Doosan Enerbility Co., Ltd. Schaufel für eine turbomaschine, schaufelanordnung und turbine

Also Published As

Publication number Publication date
JP2014109272A (ja) 2014-06-12
CN103850716B (zh) 2017-06-20
US20140154081A1 (en) 2014-06-05
CN103850716A (zh) 2014-06-11

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