EP1790827B1 - Tip shroud attachment for stator vane - Google Patents

Tip shroud attachment for stator vane Download PDF

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Publication number
EP1790827B1
EP1790827B1 EP06124935A EP06124935A EP1790827B1 EP 1790827 B1 EP1790827 B1 EP 1790827B1 EP 06124935 A EP06124935 A EP 06124935A EP 06124935 A EP06124935 A EP 06124935A EP 1790827 B1 EP1790827 B1 EP 1790827B1
Authority
EP
European Patent Office
Prior art keywords
bushing
assembly
tenons
tip shroud
shroud segment
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.)
Not-in-force
Application number
EP06124935A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP1790827A1 (en
Inventor
David C. Moorman
Joseph Moroso
William J. Miller
Jennifer Michenfelder
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 EP1790827A1 publication Critical patent/EP1790827A1/en
Application granted granted Critical
Publication of EP1790827B1 publication Critical patent/EP1790827B1/en
Not-in-force 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
    • F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/23—Manufacture essentially without removing material by permanently joining parts together
    • F05D2230/232—Manufacture essentially without removing material by permanently joining parts together by welding

Definitions

  • This invention relates to turbine stator vanes and, particularly, to a mechanical attachment between a tip shroud segment and a group of stator vanes.
  • Tip shrouds on stator vanes provide a deterministic flow path for the particular stator stage, and also serve to increase the stiffness of the vanes. It is customary to assemble arcuate shroud segments over a number of vanes (e.g., 5, 7 or more), with the segments collectively forming a 360° shroud. The tip shroud segments are typically welded to the tips of the vanes.
  • US 5421703 discloses a positively retained vane bushing for an axial flow compressor, wherein the bushing is held in place in a cylindrical-shaped opening formed between forward and aft shroud halves.
  • the bushing has an angled upper surface which is level with the surface defined by the shroud halves.
  • the upper surface of the bushing includes a slot for receiving a portion of the end of the vane which is retained in the bushing by an interference fit.
  • EP 1205638 discloses an inlet guide vane and shroud support contact, wherein each vane includes a trunnion which is received in a shroud bushing.
  • a washer is located between the bushing and a trunnion button of the vane and a shroud retainer is affixed to the inner surface of the shroud. The combination of the washer and the retainer reduces movement between the shroud and the vane.
  • each vane within a group of vanes to be covered by the shroud segment has a projecting tenon at its tip.
  • the shroud segment is formed with corresponding holes that align with the tenons of the respective vanes.
  • a bushing is seated in each of the shroud segment holes, and each bushing is formed with a center opening for receiving a respective one of the tenons.
  • the center opening is counterbored, leaving an internal shoulder or seat for the tenon.
  • the bushing is also formed with an external shoulder that allows the bushing to engage a shoulder surface of the corresponding shroud segment hole.
  • This arrangement permits the bushing to be inserted into the shroud segment hole in a direction opposite the insertion direction of the vane tenons, with the external shoulder providing a stop limit to the bushing insertion.
  • the vane tenons are subsequently welded to the internal bushing seat. Note that the bushings are not otherwise attached directly to the shroud segment but are nevertheless held in place radially by the tenon welds in one direction and the external shoulder engagement in the opposite direction.
  • the present invention relates to a stator vane segment and tip shroud segment assembly comprising: a plurality of vanes, each having an airfoil portion and a radially inner tip, each tip formed with at least one radially inwardly projecting tenon; and a tip shroud segment extending over the radially inner tips of the vanes, said tip shroud segment formed with a plurality of holes, each hole fitted with a bushing that receives a respective one of the tenons, characterised in that each bushing is formed with an internal seat on which the respective tenon is seated and each bushing is recessed relative to a radially innermost surface of said tip shroud segment such that said bushings do not protrude into a flowpath along the airfoil portions of the vanes.
  • a stator vane and tip shroud segment assembly 10 includes a plurality of stator vanes 12, each of which includes a dove tail mounting portion 14, an airfoil portion 16, and a radially projecting tenon 18 ( Figure 2 ) that projects from the radially inner tip 20 of the vane.
  • the tenon 18 is round or oval in cross section and is formed approximately intermediate the forward and trailing edges 22, 24 of the airfoil portion.
  • An arcuate tip shroud segment 26 spans and is attached to a selected member of stator vanes 12, such that the collective stator vane and tip shroud segments will form a 360° stator assembly.
  • the arcuate tip shroud segment 26 is formed with a plurality of holes 28 that are appropriately located to align with the stator tenons 18. As best seen in Figure 3 , the holes 28 are counterbored in a radially outward direction to create a radially inwardly facing shoulder 30 that is adapted to be engaged by a corresponding radially outwardly facing shoulder 32 on a bushing 34.
  • the bushing 34 is correspondingly shaped to be received in the segment hole 28 (i.e., round or oval), and, as already indicated above, is formed with an external shoulder 32 that engages the corresponding shoulder 30 on the arcuate tip shroud segment 26.
  • the bushing 34 is also formed with a center opening 36 that is counterbored to provide an annular (or oval)-shaped, radially outwardly facing seat 38 that is adapted to be engaged by the marginal edge of a respective tenon end face 40.
  • the bushing may be constructed of 316 Stainless Steel while the airfoil portion 16 (including the tenons 18) and the tip shroud segment 26 may be constructed of a harder 403 Stainless Steel, but the material compositions may vary.
  • Figures 4 and 5 illustrate another embodiment of a vane and tip shroud segment assembly 110 where the shapes of the tip shroud segment, bushing, and airfoil tenon as shown vary somewhat from the embodiment shown in Figures 1-3 . Otherwise, the components and the interaction between the tip shroud segment, airfoil portion and bushing remains as previously described. For convenience, similar reference numerals are used, but with the prefix "1" added, to designate corresponding features, but no further description is required.
  • FIG. 6 illustrates another vane segment configuration that incorporates the subject invention.
  • similar reference numerals are used to designate similar components, where applicable, but with the prefix "2" added.
  • the vane and tip shroud segment assembly 210 incorporates bushings 234 as described in connection with Figures 1-3 and this aspect of the assembly need not be repeated here.
  • the portion (or dovetail mounting portions) 214 of the vanes are ganged together via a strap 244 and a plurality of bolts 246.
  • the tenons could be formed with subtenons that project beyond the tenon end face and the extended subtenon may then be cold formed about the bushing end face.
  • the tenon could be formed with a tapped hole with a bolt passing through the center opening of the bushing and into a threaded hole in the tenon.

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)
EP06124935A 2005-11-29 2006-11-28 Tip shroud attachment for stator vane Not-in-force EP1790827B1 (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US11/288,400 US20070122274A1 (en) 2005-11-29 2005-11-29 Tip shroud attachment for stator vane

Publications (2)

Publication Number Publication Date
EP1790827A1 EP1790827A1 (en) 2007-05-30
EP1790827B1 true EP1790827B1 (en) 2009-04-15

Family

ID=37695991

Family Applications (1)

Application Number Title Priority Date Filing Date
EP06124935A Not-in-force EP1790827B1 (en) 2005-11-29 2006-11-28 Tip shroud attachment for stator vane

Country Status (4)

Country Link
US (1) US20070122274A1 (ja)
EP (1) EP1790827B1 (ja)
JP (1) JP2007146848A (ja)
DE (1) DE602006006271D1 (ja)

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP5091615B2 (ja) * 2007-10-15 2012-12-05 三菱重工業株式会社 静翼環セグメントの組立方法、静翼環セグメント、結合部材、溶接方法
US8662819B2 (en) * 2008-12-12 2014-03-04 United Technologies Corporation Apparatus and method for preventing cracking of turbine engine cases
US8696311B2 (en) 2011-03-29 2014-04-15 Pratt & Whitney Canada Corp. Apparatus and method for gas turbine engine vane retention
US9506361B2 (en) 2013-03-08 2016-11-29 Pratt & Whitney Canada Corp. Low profile vane retention
DE102015205424A1 (de) 2015-03-25 2016-09-29 Ebm-Papst Mulfingen Gmbh & Co. Kg Nachleitrad
US11260328B2 (en) 2016-11-11 2022-03-01 Briggs & Stratton, Llc Cyclonic air filter assembly for an engine
WO2019147219A1 (en) 2018-01-23 2019-08-01 Siemens Aktiengesellschaft Slide on shroud cover segments for gas turbine compressor stator vanes

Family Cites Families (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4395195A (en) * 1980-05-16 1983-07-26 United Technologies Corporation Shroud ring for use in a gas turbine engine
US4832568A (en) * 1982-02-26 1989-05-23 General Electric Company Turbomachine airfoil mounting assembly
US4798320A (en) * 1985-09-20 1989-01-17 Allied-Signal Inc. Ceramic-metal brazed joint for turbochargers
US5411368A (en) * 1993-11-08 1995-05-02 Allied-Signal Inc. Ceramic-to-metal stator vane assembly with braze
US5421703A (en) * 1994-05-25 1995-06-06 General Electric Company Positively retained vane bushing for an axial flow compressor
US5593275A (en) * 1995-08-01 1997-01-14 General Electric Company Variable stator vane mounting and vane actuation system for an axial flow compressor of a gas turbine engine
CA2284759C (en) * 1998-10-05 2006-11-28 Mahmud U. Islam Process for manufacturing or repairing turbine engine or compressor components
US6128820A (en) * 1998-10-20 2000-10-10 General Electric Co. Method of repairing damaged turbine rotor wheels using differentially controlled temperatures
US6086327A (en) * 1999-01-20 2000-07-11 Mack Plastics Corporation Bushing for a jet engine vane
US6413043B1 (en) * 2000-11-09 2002-07-02 General Electric Company Inlet guide vane and shroud support contact
US6526657B2 (en) * 2001-05-07 2003-03-04 General Electric Company Methods for automated peening of tenons connecting turbine buckets and cover plates
US6682299B2 (en) * 2001-11-15 2004-01-27 General Electric Company Variable stator vane support arrangement

Also Published As

Publication number Publication date
DE602006006271D1 (de) 2009-05-28
US20070122274A1 (en) 2007-05-31
EP1790827A1 (en) 2007-05-30
JP2007146848A (ja) 2007-06-14

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