EP2628902A2 - Schaufel mit Deckband und zugehöriges Turbinensystem - Google Patents

Schaufel mit Deckband und zugehöriges Turbinensystem Download PDF

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Publication number
EP2628902A2
EP2628902A2 EP13155135.0A EP13155135A EP2628902A2 EP 2628902 A2 EP2628902 A2 EP 2628902A2 EP 13155135 A EP13155135 A EP 13155135A EP 2628902 A2 EP2628902 A2 EP 2628902A2
Authority
EP
European Patent Office
Prior art keywords
tip
airfoil
tip shroud
shroud
axis
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Withdrawn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
EP13155135.0A
Other languages
English (en)
French (fr)
Other versions
EP2628902A3 (de
Inventor
Vineet Ninad Ghate
Harish Bommonakatte
Matthew Robert Piersall
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 EP2628902A2 publication Critical patent/EP2628902A2/de
Publication of EP2628902A3 publication Critical patent/EP2628902A3/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Withdrawn legal-status Critical Current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
    • F01D5/22—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
    • F05D2250/30—Arrangement of components
    • F05D2250/31—Arrangement of components according to the direction of their main axis or their axis of rotation
    • F05D2250/314—Arrangement of components according to the direction of their main axis or their axis of rotation the axes being inclined in relation to each other

Definitions

  • the subject matter disclosed herein relates to turbine systems, and more particularly to tip shrouds.
  • Gas turbine buckets or blades are airfoil-shaped components designed to convert thermal and kinetic energy of flow gases into mechanical rotation of the rotor. Turbine performance may be enhanced by providing a seal at the tip of the airfoil to block the flow of air over the tip of the airfoil which would otherwise bypass the airfoil and thus not perform any work on the rotor. Thus, such tip seals reduce the gap between the bucket and the surrounding stationary casing.
  • a tip shroud is provided to the tip of the airfoil and adjacent turbine buckets are aligned in a cold assembly condition.
  • the tip shrouds tend to have some degree of misalignment. Radial misalignment between two adjacent shrouds will cause obstruction in a main flow path, leading to inefficiency and possibly disengagement. Tangential misalignment will lead to a leakage area for air that therefore does not perform work on the rotor.
  • a tip shrouded blade includes an airfoil rotatable about an axial centerline. Also included is a tip shroud connected at a radially outer tip of the airfoil, wherein the tip shroud includes at least one portion angled about a tangential axis defined by the radially outer tip of the airfoil.
  • a tip shrouded blade includes an airfoil extending away from and rotatable about an axial centerline. Also included is a tip shroud provided at a tip of the airfoil, wherein the tip shroud is tilted about a tangential axis and twisted about a radial axis.
  • a turbine system having at least one row of circumferentially aligned tip shrouded blades includes a first turbine bucket having a first airfoil. Also included is a first tip shroud provided at an outer tip of the first airfoil, wherein the first tip shroud is angled about a tangential axis defined by the outer tip of the first airfoil. Further included is a second turbine bucket having a second airfoil disposed adjacent to the first airfoil. Yet further included is a second tip shroud provided at an outer tip of the second airfoil, wherein the second tip shroud is angled to correspond to the first tip shroud during a steady state operation of the turbine system.
  • a gas turbine bucket 10 is illustrated and includes an airfoil 12.
  • the airfoil 12 intercepts a flow of gases that are generated by, and delivered from, upstream components within a turbine system, such as a compressor and combustor (each not illustrated).
  • the airfoil 12 functions as a windmill vane to convert the energy of the flow of gases into tangential motion, which in turn rotates a rotor to which the gas turbine bucket 10 is attached.
  • Proximate an outer tip 14 of the airfoil 12 is disposed a tip shroud 16.
  • the tip shroud 16 includes a seal rail 18 that extends generally along the outer tip 14 of the airfoil 12, and therefore along the tip shroud 16.
  • the turbine system includes a plurality of rows of circumferentially aligned turbine buckets 10.
  • the seal rail 18 extends circumferentially around at least one of the plurality of rows, beyond the airfoil 12 sufficiently to relatively match up with seal rails 18 provided at the outer tip 14 of adjacent airfoils 12, thereby blocking flow from bypassing the row so that airflow must be directed to the length of the airfoil 12, ensuring more efficient rotation of the rotor.
  • the airfoil 12 rotates in a direction 20 about an axial centerline 22 of the turbine system.
  • a tangential axis 24 and an axial axis 26 at the outer tip 14 of the airfoil 12 are formed relative to the direction 20 of rotation of the outer tip 14.
  • the axial axis 26 extends in the axial direction of the turbine system and is parallel to the axial centerline 22.
  • a radial axis 27 extends in a longitudinal direction of the airfoil 12, and specifically an axis extending radially outward from the axial centerline 22 toward the tip shroud 16.
  • the turbine buckets 10 and the tip shrouds 16 are subjected to significant forces and thermal stresses that result in asymmetric deflections of the tip shrouds 16.
  • Such asymmetric deflections of the tip shrouds 16 cause misalignment between adjacent tip shrouds 16, resulting in inefficiency and/or stress imbalance which can lead to material creep.
  • the tip shroud 16 is assembled in a cold, non-operating condition, such that it is configured to be tilted about the axial axis 26.
  • the tip shroud 16 includes a front region 28 and a rear region 30, with respect to the direction 20 of rotation of the airfoil 12.
  • the direction and magnitude of tilt of the tip shroud 16 is determined by the application of use and is set based on experimentation and analysis showing the magnitude and direction of deflection occurring under various operating conditions.
  • the tip shroud 16 is tilted forwardly in a cold, non-operating condition, such that the front region 28 is closer to the rotor or axial centerline 22 of the turbine system than the rear region 30, however, this forward tilting is merely for illustrative purposes and it should be appreciated that rearward tilting is contemplated.
  • the tip shroud 16 rotates due to the previously described forces and thermal loads imposed thereon.
  • Such pre-tilting and rotation of the tip shroud 16 reduces the degree of misalignment of adjacent tip shrouds 16 during operation. Pre-tilting results in advantageous alignment of adjacent tip shrouds 16.
  • the tip shroud 16 in addition to tilting about the axial axis 26, the tip shroud 16 is assembled in a cold, non-operating condition, such that it is configured to be tilted about the tangential axis 24.
  • the tip shroud 16 includes an upstream region 32 and a downstream region 34.
  • the direction and magnitude of tilt of the tip shroud 16 about the tangential axis 24 is determined by the application of use.
  • the tip shroud 16 is tilted in an upstream direction, such that the upstream region 32 is closer to the rotor or axial centerline 22 of the turbine system than the downstream region 34, however, this upstream tilting is merely for illustrative purposes and it should be appreciated that downstream tilting is contemplated. Similar to the effect of tilting about the axial axis 26, tilting about the tangential axis 24 reduces the degree of misalignment between components. Additionally, the tip shroud 16 is pre-twisted about the radial axis 27, such that desirable orientation of the tip shroud 16 occurs during operation of the turbine bucket 10.
  • the degree of angling may vary based on the application, however, it is contemplated that such angles will range between +/- 10 degrees in either direction of rotation about a respective axis, and more typically between +/- 5 degrees in either direction of rotation.
  • the tip shroud 16 may take on various configurations and features, including a recess 40 proximate the rear region 30 of the tip shroud 16 that is configured to allow a protrusion 42 from the front region 28 of an adjacent tip shroud 16 to optionally be disposed therein. Such an arrangement permits the rotational movement of the tip shrouds 16 relative to one another during operation of the turbine bucket 10.
  • the tip shroud 16 it is advantageous to pre-tilt or pre-twist the tip shroud 16 to account for deformations that occur during operation of the turbine bucket 10, particularly about multiple axes, such as the axial axis 26, the radial axis 27 and the tangential axis 24.
  • axes such as the axial axis 26, the radial axis 27 and the tangential axis 24.
  • the tip shroud 16 merely need be rotated about some axis that is offset in any direction from that of the axial centerline 22. This refers to axes of rotation that are shifted radially, tangentially, or axially from the axial centerline 22.
  • the tip shroud 16 is configured such that it may deflect into a relatively planar member during steady-state operation and oriented within a plane tangential to the outer tip 14 of the airfoil 12.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP13155135.0A 2012-02-15 2013-02-13 Schaufel mit Deckband und zugehöriges Turbinensystem Withdrawn EP2628902A3 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US13/397,296 US20130209258A1 (en) 2012-02-15 2012-02-15 Tip shrouded blade

Publications (2)

Publication Number Publication Date
EP2628902A2 true EP2628902A2 (de) 2013-08-21
EP2628902A3 EP2628902A3 (de) 2017-05-10

Family

ID=47683642

Family Applications (1)

Application Number Title Priority Date Filing Date
EP13155135.0A Withdrawn EP2628902A3 (de) 2012-02-15 2013-02-13 Schaufel mit Deckband und zugehöriges Turbinensystem

Country Status (5)

Country Link
US (1) US20130209258A1 (de)
EP (1) EP2628902A3 (de)
JP (1) JP6259189B2 (de)
CN (1) CN103256078A (de)
RU (1) RU2013106198A (de)

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10774654B2 (en) * 2015-07-31 2020-09-15 General Electric Company Cooling arrangements in turbine blades
US10648346B2 (en) * 2016-07-06 2020-05-12 General Electric Company Shroud configurations for turbine rotor blades

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5238366A (en) * 1992-07-06 1993-08-24 Westinghouse Electric Corp. Method and apparatus for determining turbine blade deformation
US7654797B2 (en) * 2004-09-08 2010-02-02 Alstom Technology Ltd Blade with shroud
US20100061861A1 (en) * 2008-09-08 2010-03-11 General Electric Company Steam turbine rotating blade for a low pressure section of a steam turbine engine

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP3178327B2 (ja) * 1996-01-31 2001-06-18 株式会社日立製作所 蒸気タービン
JP2004052757A (ja) * 2002-05-31 2004-02-19 Toshiba Corp タービン動翼
JP2005214205A (ja) * 2004-01-31 2005-08-11 United Technol Corp <Utc> 回転機械用のロータブレード
US7134838B2 (en) * 2004-01-31 2006-11-14 United Technologies Corporation Rotor blade for a rotary machine
US7066713B2 (en) * 2004-01-31 2006-06-27 United Technologies Corporation Rotor blade for a rotary machine
US7344359B2 (en) * 2005-06-02 2008-03-18 General Electric Company Methods and systems for assembling shrouded turbine bucket and tangential entry dovetail
US7771160B2 (en) * 2006-08-10 2010-08-10 United Technologies Corporation Ceramic shroud assembly

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5238366A (en) * 1992-07-06 1993-08-24 Westinghouse Electric Corp. Method and apparatus for determining turbine blade deformation
US7654797B2 (en) * 2004-09-08 2010-02-02 Alstom Technology Ltd Blade with shroud
US20100061861A1 (en) * 2008-09-08 2010-03-11 General Electric Company Steam turbine rotating blade for a low pressure section of a steam turbine engine

Also Published As

Publication number Publication date
US20130209258A1 (en) 2013-08-15
CN103256078A (zh) 2013-08-21
EP2628902A3 (de) 2017-05-10
RU2013106198A (ru) 2014-08-20
JP6259189B2 (ja) 2018-01-10
JP2013167246A (ja) 2013-08-29

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