US20070122274A1 - Tip shroud attachment for stator vane - Google Patents

Tip shroud attachment for stator vane Download PDF

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Publication number
US20070122274A1
US20070122274A1 US11/288,400 US28840005A US2007122274A1 US 20070122274 A1 US20070122274 A1 US 20070122274A1 US 28840005 A US28840005 A US 28840005A US 2007122274 A1 US2007122274 A1 US 2007122274A1
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US
United States
Prior art keywords
bushing
tip shroud
assembly
shroud segment
tip
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.)
Abandoned
Application number
US11/288,400
Inventor
C. Moorman
Joseph Moroso
William 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
Priority to US11/288,400 priority Critical patent/US20070122274A1/en
Assigned to GENERAL ELECTRIC COMPANY reassignment GENERAL ELECTRIC COMPANY ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: MICHENFELDER, JENNIFER, MILLER, WILLIAM J., MOORMAN, C. DAVID, MOROSO, JOSEPH
Priority to EP06124935A priority patent/EP1790827B1/en
Priority to DE602006006271T priority patent/DE602006006271D1/en
Priority to JP2006320957A priority patent/JP2007146848A/en
Publication of US20070122274A1 publication Critical patent/US20070122274A1/en
Abandoned 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
    • 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.
  • 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.
  • the invention in another aspect, 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; a tip shroud segment extending over the radially inner tips of the vanes; the tip shroud segment formed with a plurality of holes, each hole fitted with a bushing that receives a respective one of the tenons; wherein the bushing is formed with an internal shoulder on which the respective tenon is seated; and wherein each bushing is formed with an external shoulder engaged by the tip shroud segment.
  • the invention in still another aspect, 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; a tip shroud segment extending over the radially inner tips of the vanes, the tip shroud segment formed with a plurality of holes, each hole fitted with a bushing that receives a respective one of the tenons; wherein each bushing is formed with an external shoulder engaged by the tip shroud; and wherein each bushing is formed with a center hole counterbored to provide an internal shoulder that provides a seat for the respective tenon and wherein the tenon is welded to the bushing at the internal shoulder.
  • FIG. 1 discloses a perspective view of a shrouded stator vane segment in accordance with an exemplary embodiment of the invention
  • FIG. 2 is a cross-section taken along the line 2 - 2 of FIG. 1 ;
  • FIG. 3 is a partial cross-section taken along the line 3 - 3 in FIG. 1 ;
  • FIG. 4 is a perspective view of another exemplary embodiment of the invention.
  • FIG. 5 is an enlarged detail similar to FIG. 3 but taken from the assembly shown in FIG. 4 ;
  • FIG. 6 is a perspective view of still another embodiment of the invention.
  • 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 ( FIG. 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 .
  • 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 airfoil tenons 18 are inserted into the bushing in direction B until the tenons are fully engaged with the seats 38 . Subsequently, each airfoil tenon 18 is fixed to the bushing at the seat 38 by weld 42 . It is significant that the bushing is not otherwise fixed to the tip shroud segment 26 . As a result, some degree of movement between the airfoil portion 16 and the tip shroud segment 26 is permitted via bushing 34 , thereby reducing stresses during operation. Note that the bushing is recessed relative to the radially inner face of the shroud segment so as not to protrude into the gas flowpath.
  • 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.
  • FIGS. 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 FIGS. 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 FIGS. 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.

Abstract

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, the tip shroud segment formed with a plurality of holes, each hole fitted with a bushing that receives a respective one of the tenons.

Description

    BACKGROUND OF THE INVENTION
  • 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.
    • BRIEF SUMMARY OF THE INVENTION
  • In accordance with an exemplary embodiment of this invention, 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.
  • Accordingly in one aspect, 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.
  • In another aspect, the 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; a tip shroud segment extending over the radially inner tips of the vanes; the tip shroud segment formed with a plurality of holes, each hole fitted with a bushing that receives a respective one of the tenons; wherein the bushing is formed with an internal shoulder on which the respective tenon is seated; and wherein each bushing is formed with an external shoulder engaged by the tip shroud segment.
  • In still another aspect, the 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; a tip shroud segment extending over the radially inner tips of the vanes, the tip shroud segment formed with a plurality of holes, each hole fitted with a bushing that receives a respective one of the tenons; wherein each bushing is formed with an external shoulder engaged by the tip shroud; and wherein each bushing is formed with a center hole counterbored to provide an internal shoulder that provides a seat for the respective tenon and wherein the tenon is welded to the bushing at the internal shoulder.
  • The invention will now be described in connection with the drawings identified below.
    • BRIEF DESCRIPTION OF THE DRAWING
  • FIG. 1 discloses a perspective view of a shrouded stator vane segment in accordance with an exemplary embodiment of the invention;
  • FIG. 2 is a cross-section taken along the line 2-2 of FIG. 1;
  • FIG. 3 is a partial cross-section taken along the line 3-3 in FIG. 1;
  • FIG. 4 is a perspective view of another exemplary embodiment of the invention; and
  • FIG. 5 is an enlarged detail similar to FIG. 3 but taken from the assembly shown in FIG. 4; and
  • FIG. 6 is a perspective view of still another embodiment of the invention.
    • DETAILED DESCRIPTION OF THE DRAWINGS
  • With reference initially to FIGS. 1-3, 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 (FIG. 2) that projects from the radially inner tip 20 of the vane. Typically, 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 FIG. 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.
  • With the bushings 34 inserted in the segment holes 28 in direction A (FIG. 3), the airfoil tenons 18 are inserted into the bushing in direction B until the tenons are fully engaged with the seats 38. Subsequently, each airfoil tenon 18 is fixed to the bushing at the seat 38 by weld 42. It is significant that the bushing is not otherwise fixed to the tip shroud segment 26. As a result, some degree of movement between the airfoil portion 16 and the tip shroud segment 26 is permitted via bushing 34, thereby reducing stresses during operation. Note that the bushing is recessed relative to the radially inner face of the shroud segment so as not to protrude into the gas flowpath.
  • In the exemplary embodiment, 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.
  • FIGS. 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 FIGS. 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. In this figure, 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 FIGS. 1-3 and this aspect of the assembly need not be repeated here. In this embodiment, the portion (or dovetail mounting portions) 214 of the vanes are ganged together via a strap 244 and a plurality of bolts 246.
  • In an alternative arrangement that does not require welding, 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. In yet another variation, 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.
  • While the invention has been described in connection with what is presently considered to be the most practical and preferred embodiment, it is to be understood that the invention is not to be limited to the disclosed embodiment, but on the contrary, is intended to cover various modifications and equivalent arrangements included within the spirit and scope of the appended claims.

Claims (18)

1. 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 said tenons.
2. The assembly of claim 1 wherein said tenons are attached directly to said bushings.
3. The assembly of claim 1 wherein said bushing is formed with an internal shoulder on which the respective tenon is seated.
4. The assembly of claim 1 wherein each bushing is recessed relative to a radially innermost surface of said tip shroud segment such that said bushing does not protrude into a flowpath along the airfoil portions of the vanes.
5. The assembly of claim 3 wherein each bushing is recessed relative to a radially innermost surface of said tip shroud segment such that said bushing does not protrude into a flowpath along the airfoil portions of the vanes.
6. The assembly of claim 1 wherein each bushing is formed with an external shoulder engaged by said tip shroud segment.
7. The assembly of claim 3 wherein each bushing is formed with an external shoulder engaged by said tip shroud segment.
8. The assembly of claim 1 wherein each bushing is formed with a center hole counterbored to provide an internal shoulder that provides a seat for the respective tenon and wherein said tenon is welded to said bushing at said internal shoulder.
9. The assembly of claim 2 wherein said bushings are not otherwise attached to said tip shroud segment.
10. The assembly of claim 1 wherein said tenons are welded to said bushings.
11. 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;
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 said tenons;
wherein said bushing is formed with an internal shoulder on which the respective tenon is seated; and
wherein each bushing is formed with an external shoulder engaged by said tip shroud segment.
12. The assembly of claim 10 wherein said tenons are fixed to said bushings.
13. The assembly of claim 10 wherein each bushing is recessed relative to a radially innermost surface of said tip shroud segment such that said bushing does not protrude into a flowpath along the airfoil portions of the vanes.
14. The assembly of claim 11 wherein each bushing is recessed relative to a radially innermost surface of said tip shroud segment such that said bushing does not protrude into a flowpath along the airfoil portions of the vanes.
15. The assembly of claim 11 wherein each bushing is formed with a center hole counterbored to provide an internal shoulder that provides a seat for the respective tenon and wherein said tenon is welded to said bushing at said internal shoulder.
16. 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;
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 said tenons;
wherein each bushing is formed with an external shoulder engaged by said tip shroud; and
wherein each bushing is formed with a center hole counterbored to provide an internal shoulder that provides a seat for the respective tenon and wherein said tenon is welded to said bushing at said internal shoulder.
17. The assembly of claim 16, wherein each bushing is recessed relative to a radially innermost surface of said tip shroud such that said bushing does not protrude into a flowpath along the airfoil portions of the vanes.
18. The assembly of claim 16 wherein each vane has an attachment portion, and wherein a strap extends across the attachment portions of the respective plurality of vanes, said strap attached to each of the attachment portions.
US11/288,400 2005-11-29 2005-11-29 Tip shroud attachment for stator vane Abandoned US20070122274A1 (en)

Priority Applications (4)

Application Number Priority Date Filing Date Title
US11/288,400 US20070122274A1 (en) 2005-11-29 2005-11-29 Tip shroud attachment for stator vane
EP06124935A EP1790827B1 (en) 2005-11-29 2006-11-28 Tip shroud attachment for stator vane
DE602006006271T DE602006006271D1 (en) 2005-11-29 2006-11-28 Shroud attachment for a vane
JP2006320957A JP2007146848A (en) 2005-11-29 2006-11-29 Tip shroud attachment device for vane

Applications Claiming Priority (1)

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US11/288,400 US20070122274A1 (en) 2005-11-29 2005-11-29 Tip shroud attachment for stator vane

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US20070122274A1 true US20070122274A1 (en) 2007-05-31

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US11/288,400 Abandoned US20070122274A1 (en) 2005-11-29 2005-11-29 Tip shroud attachment for stator vane

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US (1) US20070122274A1 (en)
EP (1) EP1790827B1 (en)
JP (1) JP2007146848A (en)
DE (1) DE602006006271D1 (en)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20100135782A1 (en) * 2007-10-15 2010-06-03 Ikuo Nakamura Assembling method of stator blade ring segment, stator blade ring segment, coupling member, welding method
US20100196149A1 (en) * 2008-12-12 2010-08-05 United Technologies Corporation Apparatus and Method for Preventing Cracking of Turbine Engine Cases
DE102015205424A1 (en) * 2015-03-25 2016-09-29 Ebm-Papst Mulfingen Gmbh & Co. Kg vane
WO2019147219A1 (en) 2018-01-23 2019-08-01 Siemens Aktiengesellschaft Slide on shroud cover segments for gas turbine compressor stator vanes
US11260328B2 (en) 2016-11-11 2022-03-01 Briggs & Stratton, Llc Cyclonic air filter assembly for an engine

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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

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US4798320A (en) * 1985-09-20 1989-01-17 Allied-Signal Inc. Ceramic-metal brazed joint for turbochargers
US4832568A (en) * 1982-02-26 1989-05-23 General Electric Company Turbomachine airfoil mounting assembly
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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
US6086327A (en) * 1999-01-20 2000-07-11 Mack Plastics Corporation Bushing for a jet engine vane
US6269540B1 (en) * 1998-10-05 2001-08-07 National Research Council Of Canada Process for manufacturing or repairing turbine engine or compressor components
US6413043B1 (en) * 2000-11-09 2002-07-02 General Electric Company Inlet guide vane and shroud support contact
US6494683B1 (en) * 1998-10-20 2002-12-17 General Electric Company Repaired turbine rotor wheel
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

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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
US6269540B1 (en) * 1998-10-05 2001-08-07 National Research Council Of Canada Process for manufacturing or repairing turbine engine or compressor components
US6494683B1 (en) * 1998-10-20 2002-12-17 General Electric Company Repaired turbine rotor wheel
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

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20100135782A1 (en) * 2007-10-15 2010-06-03 Ikuo Nakamura Assembling method of stator blade ring segment, stator blade ring segment, coupling member, welding method
US8215904B2 (en) * 2007-10-15 2012-07-10 Mitsubishi Heavy Industries, Ltd. Assembling method of stator blade ring segment, stator blade ring segment, coupling member, welding method
US20100196149A1 (en) * 2008-12-12 2010-08-05 United Technologies Corporation Apparatus and Method for Preventing Cracking of Turbine Engine Cases
US8662819B2 (en) * 2008-12-12 2014-03-04 United Technologies Corporation Apparatus and method for preventing cracking of turbine engine cases
DE102015205424A1 (en) * 2015-03-25 2016-09-29 Ebm-Papst Mulfingen Gmbh & Co. Kg vane
US10760590B2 (en) 2015-03-25 2020-09-01 Ebm-Papst Mulfingen Gmbh & Co. Kg Flow straightener
US11260328B2 (en) 2016-11-11 2022-03-01 Briggs & Stratton, Llc Cyclonic air filter assembly for an engine
US11712649B2 (en) 2016-11-11 2023-08-01 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

Also Published As

Publication number Publication date
JP2007146848A (en) 2007-06-14
EP1790827B1 (en) 2009-04-15
DE602006006271D1 (en) 2009-05-28
EP1790827A1 (en) 2007-05-30

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