US20080317597A1 - Domed tip cap and related method - Google Patents

Domed tip cap and related method Download PDF

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Publication number
US20080317597A1
US20080317597A1 US11/819,030 US81903007A US2008317597A1 US 20080317597 A1 US20080317597 A1 US 20080317597A1 US 81903007 A US81903007 A US 81903007A US 2008317597 A1 US2008317597 A1 US 2008317597A1
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US
United States
Prior art keywords
tip cap
bucket
airfoil portion
outer end
radially outer
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
US11/819,030
Inventor
Louis Veltre
William S. Zemitis
Gary C. Liotta
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 US11/819,030 priority Critical patent/US20080317597A1/en
Assigned to GENERAL ELECTRIC COMPANY reassignment GENERAL ELECTRIC COMPANY ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: LIOTTA, GARY, VELTRE, LOUIS, ZEMITIS, WILLIAM S.
Priority to JP2008157347A priority patent/JP2009002339A/en
Priority to DE102008002906A priority patent/DE102008002906A1/en
Priority to CNA2008101293803A priority patent/CN101333941A/en
Publication of US20080317597A1 publication Critical patent/US20080317597A1/en
Abandoned legal-status Critical Current

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    • 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
    • F01D5/20—Specially-shaped blade tips to seal space between tips and stator
    • 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
    • F05D2230/21—Manufacture essentially without removing material by casting
    • 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
    • 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
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/221—Improvement of heat transfer
    • F05D2260/2214—Improvement of heat transfer by increasing the heat transfer surface
    • F05D2260/22141—Improvement of heat transfer by increasing the heat transfer surface using fins or ribs

Definitions

  • This invention relates to turbine technology and, more specifically, to cap constructions for turbine buckets or blades.
  • tip caps have been used to cover the tips of airfoil portions of turbine buckets that have internal serpentine cooling circuits.
  • These tip caps are manufactured from flat plate stock and are typically either welded to the radially outer end of the airfoil portion of the bucket, or cast in with the airfoil portion. In either case, the flat tip caps are subject to high stresses during operation.
  • a tip cap insert is adapted to be welded to the radially outer end of a bucket airfoil portion.
  • the tip cap is in the shape of an inverted dome, i.e., it is substantially concave in a radially inward direction (as seen from the exterior of the bucket).
  • the tip cap is also formed with a peripheral flange adapted to seat on an internal shoulder within the airfoil portion to which the tip cap is welded.
  • the domed tip cap is cast integrally with the airfoil portion and other airfoil features of the bucket.
  • a bucket for a turbine comprising a dovetail mounting portion, a shank portion defined at a radially outer end thereof by a platform, and an airfoil portion extending radially outward of the platform, the airfoil portion having a radially outer end closed by a tip cap wherein one or both of an interior and exterior surface of the tip cap is formed of a non-planar shape that reduces stress in the tip cap during use.
  • a bucket for a turbine comprising a dovetail mounting portion, a shank portion defined at a radially outer end thereof by a platform, and an airfoil portion extending radially outward of the platform, the airfoil portion having a radially outer end closed by a tip cap wherein at least an interior surface of the tip cap is domed in a radially inward direction; and wherein the tip cap is formed with one or more internal ribs.
  • a method of reducing stress in a tip cap of a turbine bucket comprising an airfoil portion of the turbine bucket with a radially outer end; and closing the radially outer end with a tip cap having a non-planar shape that reduces stress in the tip cap during use.
  • FIG. 1 is a perspective view of a conventional turbine bucket
  • FIG. 2 is an enlarged detail of the tip cap portion of the airfoil shown in FIG. 1 , shown at a slightly different angle, to make visible the planar tip cap;
  • FIG. 3 is a plan view of the airfoil portion illustrated in FIGS. 1 and 2 ;
  • FIG. 4 is a section taken along the line 4 - 4 of FIG. 3 ;
  • FIG. 5 is a top plan view of an airfoil portion of a bucket having a domed tip cap in accordance with an exemplary but non-limiting embodiment of the technology disclosed herein;
  • FIG. 6 is a partial section taken along the line 6 - 6 of FIG. 5 ;
  • FIG. 7 is a section similar to FIG. 6 , but showing the domed tip cap cast in with the airfoil portion of the bucket in accordance with another exemplary but non-limiting embodiment.
  • FIG. 8 is a section having a similar orientation as in FIGS. 6 and 7 but illustrating another tip cap shape in accordance with the invention.
  • a conventional internally cooled bucket 10 for a turbine engine comprises a mounting dovetail 12 , a shank or shank portion 14 , a platform 16 atop the shank, and an airfoil portion or airfoil 18 extending radially outwardly from the platform.
  • the airfoil 18 terminates at its outermost end with a tip cap 20 .
  • the tip cap illustrated in FIGS. 1-4 comprises a flat plate welded to the airfoil portion. More specifically, and as best seen in FIG. 4 , the flat tip cap 20 is seated on an internal peripheral shoulder or flange 22 and welded thereto in accordance with conventional welding techniques. It will be appreciated that the flat tip cap may also be cast in with the airfoil, eliminating the need for welding. Internal ribs 24 (shown in phantom) may be employed to reinforce the tip cap as necessary.
  • the bucket 110 includes an airfoil 118 with a tip cap 120 secured at the radially outermost end of the airfoil.
  • the tip cap 120 may be described as having an inverted dome shape, i.e., the tip cap is concave in a radially inward direction (or as viewed externally of the bucket). In other words, the tip cap projects radially into the interior of the bucket.
  • the tip cap 120 is formed with a peripheral flange or edge 26 that is seated on an internal shoulder or flange 122 of the airfoil 118 and, again, welded thereto in accordance with conventional welding techniques.
  • the tip cap 220 of airfoil 218 is cast in with the airfoil portion and, like the tip cap in FIG. 6 , has an inverted dome or inwardly concave shape.
  • the tip cap dome By imparting an inverted dome shape to the (i.e., planar) tip cap, bending stresses typically associated with flat tip caps can be reduced. In some cases, the stress-reducing benefit of the dome cap may be sufficient to justify elimination of rib welds that are traditionally used to secure the tip caps to their respective airfoils. It will be appreciated that the curvature of the tip cap dome is optimized to provide stress reduction to all regions of the tip cap, regardless of the span being covered.
  • the domed tip cap may be provided with known surface features (such as turbulators) to enhance convection (see, for example, internal ribs 122 in FIG. 3 and 124 in FIG. 5 ).
  • FIG. 8 illustrates another exemplary, non-limiting implementation where the tip cap 320 of bucket 318 is curved inwardly on its outer surface 321 while remaining flat on its inner surface 323 .
  • This shape also provides the desired stress reduction.
  • the term “domed” is intended to embrace any number of shapes for one or both of the interior and exterior surfaces of a bucket tip cap (whether welded to or cast in with the airfoil portion of the bucket), that may include circular, parabolas, or otherwise complex shapes that deviate from the traditional flat plate stock and that reduce stress.
  • the dome shape of the tip cap also enables a reduction in required material capability and/or material thickness, and increased operating temperatures of the tip cap may be possible without altering the material composition.
  • wider openings can be covered than with flat designs of the same material and thickness.

Abstract

A bucket for a turbine includes a dovetail mounting portion, a shank portion defined at a radially outer end thereof by a platform, and an airfoil portion extending radially outward of the platform. The airfoil portion has a radially outer end closed by a tip cap having a non-planar shape that reduces stress in the tip cap during use. A related method of reducing stress in a tip cap of a turbine bucket includes providing an airfoil portion of the turbine bucket with a radially outer end; and closing the radially outer end with a tip cap having a non-planar shape that reduces stress in the tip cap during use.

Description

    BACKGROUND
  • This invention relates to turbine technology and, more specifically, to cap constructions for turbine buckets or blades. Traditionally, tip caps have been used to cover the tips of airfoil portions of turbine buckets that have internal serpentine cooling circuits. These tip caps are manufactured from flat plate stock and are typically either welded to the radially outer end of the airfoil portion of the bucket, or cast in with the airfoil portion. In either case, the flat tip caps are subject to high stresses during operation.
    • BRIEF SUMMARY OF THE INVENTION
  • In one exemplary but non-limiting embodiment, a tip cap insert is adapted to be welded to the radially outer end of a bucket airfoil portion. In accordance with this embodiment, the tip cap is in the shape of an inverted dome, i.e., it is substantially concave in a radially inward direction (as seen from the exterior of the bucket).
  • The tip cap is also formed with a peripheral flange adapted to seat on an internal shoulder within the airfoil portion to which the tip cap is welded.
  • In another exemplary but non-limiting embodiment, the domed tip cap is cast integrally with the airfoil portion and other airfoil features of the bucket.
  • Accordingly, in one aspect, there is provided a bucket for a turbine comprising a dovetail mounting portion, a shank portion defined at a radially outer end thereof by a platform, and an airfoil portion extending radially outward of the platform, the airfoil portion having a radially outer end closed by a tip cap wherein one or both of an interior and exterior surface of the tip cap is formed of a non-planar shape that reduces stress in the tip cap during use.
  • In another aspect, there is provided a bucket for a turbine comprising a dovetail mounting portion, a shank portion defined at a radially outer end thereof by a platform, and an airfoil portion extending radially outward of the platform, the airfoil portion having a radially outer end closed by a tip cap wherein at least an interior surface of the tip cap is domed in a radially inward direction; and wherein the tip cap is formed with one or more internal ribs.
  • In still another aspect, there is provided a method of reducing stress in a tip cap of a turbine bucket comprising an airfoil portion of the turbine bucket with a radially outer end; and closing the radially outer end with a tip cap having a non-planar shape that reduces stress in the tip cap during use.
  • A more detailed description will now be provided in connection with the drawings identified below.
    • BRIEF DESCRIPTION OF THE DRAWINGS
  • FIG. 1 is a perspective view of a conventional turbine bucket;
  • FIG. 2 is an enlarged detail of the tip cap portion of the airfoil shown in FIG. 1, shown at a slightly different angle, to make visible the planar tip cap;
  • FIG. 3 is a plan view of the airfoil portion illustrated in FIGS. 1 and 2;
  • FIG. 4 is a section taken along the line 4-4 of FIG. 3;
  • FIG. 5 is a top plan view of an airfoil portion of a bucket having a domed tip cap in accordance with an exemplary but non-limiting embodiment of the technology disclosed herein;
  • FIG. 6 is a partial section taken along the line 6-6 of FIG. 5;
  • FIG. 7 is a section similar to FIG. 6, but showing the domed tip cap cast in with the airfoil portion of the bucket in accordance with another exemplary but non-limiting embodiment; and
  • FIG. 8 is a section having a similar orientation as in FIGS. 6 and 7 but illustrating another tip cap shape in accordance with the invention.
    •  DETAILED DESCRIPTION OF THE DRAWINGS
  • With reference to FIGS. 1-4, a conventional internally cooled bucket 10 for a turbine engine comprises a mounting dovetail 12, a shank or shank portion 14, a platform 16 atop the shank, and an airfoil portion or airfoil 18 extending radially outwardly from the platform. The airfoil 18 terminates at its outermost end with a tip cap 20. The tip cap illustrated in FIGS. 1-4 comprises a flat plate welded to the airfoil portion. More specifically, and as best seen in FIG. 4, the flat tip cap 20 is seated on an internal peripheral shoulder or flange 22 and welded thereto in accordance with conventional welding techniques. It will be appreciated that the flat tip cap may also be cast in with the airfoil, eliminating the need for welding. Internal ribs 24 (shown in phantom) may be employed to reinforce the tip cap as necessary.
  • Turning now to FIGS. 5 and 6, a tip cap in accordance with an exemplary but non-limiting embodiment of this invention is illustrated. For convenience, reference numerals corresponding to those used in FIGS. 1-4 are used in FIGS. 5 and 6 to designate common components, but with a prefix 1 added. Thus, the bucket 110 includes an airfoil 118 with a tip cap 120 secured at the radially outermost end of the airfoil. The tip cap 120 may be described as having an inverted dome shape, i.e., the tip cap is concave in a radially inward direction (or as viewed externally of the bucket). In other words, the tip cap projects radially into the interior of the bucket. The tip cap 120 is formed with a peripheral flange or edge 26 that is seated on an internal shoulder or flange 122 of the airfoil 118 and, again, welded thereto in accordance with conventional welding techniques.
  • In another exemplary but non-limiting embodiment illustrated in FIG. 7, the tip cap 220 of airfoil 218 is cast in with the airfoil portion and, like the tip cap in FIG. 6, has an inverted dome or inwardly concave shape.
  • By imparting an inverted dome shape to the (i.e., planar) tip cap, bending stresses typically associated with flat tip caps can be reduced. In some cases, the stress-reducing benefit of the dome cap may be sufficient to justify elimination of rib welds that are traditionally used to secure the tip caps to their respective airfoils. It will be appreciated that the curvature of the tip cap dome is optimized to provide stress reduction to all regions of the tip cap, regardless of the span being covered. In addition, the domed tip cap may be provided with known surface features (such as turbulators) to enhance convection (see, for example, internal ribs 122 in FIG. 3 and 124 in FIG. 5).
  • FIG. 8 illustrates another exemplary, non-limiting implementation where the tip cap 320 of bucket 318 is curved inwardly on its outer surface 321 while remaining flat on its inner surface 323. This shape also provides the desired stress reduction. Thus, it will be appreciated that the term “domed” is intended to embrace any number of shapes for one or both of the interior and exterior surfaces of a bucket tip cap (whether welded to or cast in with the airfoil portion of the bucket), that may include circular, parabolas, or otherwise complex shapes that deviate from the traditional flat plate stock and that reduce stress.
  • The dome shape of the tip cap also enables a reduction in required material capability and/or material thickness, and increased operating temperatures of the tip cap may be possible without altering the material composition. In addition, wider openings can be covered than with flat designs of the same material and thickness.
  • 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 (17)

1. A bucket for a turbine comprising a dovetail mounting portion, a shank portion defined at a radially outer end thereof by a platform, and an airfoil portion extending radially outward of said platform, said airfoil portion having a radially outer end closed by a tip cap wherein one or both of an interior and exterior surface of the tip cap is formed of a non-planar shape that reduces stress in the tip cap during use.
2. The bucket of claim 1 wherein said non-planar shape is domed in a radially inward direction.
3. The bucket of claim 2 wherein said tip cap is cast-in with said airfoil portion.
4. The bucket of claim 1 wherein said tip cap is welded to said airfoil portion.
5. The bucket of claim 4 wherein said tip cap is formed with a peripheral flange seated on a shoulder formed in said airfoil portion.
6. The bucket of claim 1 wherein said tip cap is formed with one or more internal ribs.
7. A bucket for a turbine comprising a dovetail mounting portion, a shank portion defined at a radially outer end thereof by a platform, and an airfoil portion extending radially outward of said platform, said airfoil portion having a radially outer end closed by a tip cap;
wherein at least an exterior surface of said tip cap is domed in a radially inward direction; and
wherein said tip cap is formed with one or more internal ribs.
8. The bucket of claim 7 wherein said tip cap is cast-in with said airfoil portion.
9. The bucket of claim 7 wherein said tip cap is welded to said airfoil portion.
10. The bucket of claim 9 wherein said tip cap is formed with a peripheral flange seated on a shoulder formed in said airfoil portion.
11. A method of reducing stress in a tip cap of a turbine bucket comprising providing an airfoil portion of the turbine bucket with a radially outer end; and
closing the radially outer end with a tip cap having a non-planar shape that reduces stress in the tip cap during use.
12. The method of claim 11 including welding the tip cap to the airfoil portion.
13. The method of claim 12 wherein the tip cap is seated on an internal flange in the airfoil portion.
14. The method of claim 11 wherein the tip cap is cast in with the airfoil portion.
15. The method of claim 11 wherein said tip cap is formed with one or more internal ribs.
16. The method of claim 11 wherein interior and exterior surfaces of said tip cap are domed in a radially inward direction.
17. The method of claim 11 wherein an exterior surface of said tip cap is domed in a radially inward direction.
US11/819,030 2007-06-25 2007-06-25 Domed tip cap and related method Abandoned US20080317597A1 (en)

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US11/819,030 US20080317597A1 (en) 2007-06-25 2007-06-25 Domed tip cap and related method
JP2008157347A JP2009002339A (en) 2007-06-25 2008-06-17 Dome-shaped tip cap, and related method
DE102008002906A DE102008002906A1 (en) 2007-06-25 2008-06-25 Arched tip cap and associated method
CNA2008101293803A CN101333941A (en) 2007-06-25 2008-06-25 Domed tip cap and related method

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US11/819,030 US20080317597A1 (en) 2007-06-25 2007-06-25 Domed tip cap and related method

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JP (1) JP2009002339A (en)
CN (1) CN101333941A (en)
DE (1) DE102008002906A1 (en)

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US20110076151A1 (en) * 2009-09-30 2011-03-31 General Electric Company Method and system for focused energy brazing
WO2013169754A1 (en) * 2012-05-09 2013-11-14 Siemens Energy, Inc. Repair method of a turbine blade tip
EP3313597B1 (en) * 2015-06-29 2020-06-17 Safran Aircraft Engines Method for manufacturing a blade comprising a squealer tip integrating a small wall
US11814979B1 (en) * 2022-09-21 2023-11-14 Rtx Corporation Systems and methods of hybrid blade tip repair

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Publication number Priority date Publication date Assignee Title
US20110076151A1 (en) * 2009-09-30 2011-03-31 General Electric Company Method and system for focused energy brazing
US8573949B2 (en) 2009-09-30 2013-11-05 General Electric Company Method and system for focused energy brazing
WO2013169754A1 (en) * 2012-05-09 2013-11-14 Siemens Energy, Inc. Repair method of a turbine blade tip
US9186757B2 (en) 2012-05-09 2015-11-17 Siemens Energy, Inc. Method of providing a turbine blade tip repair
EP3313597B1 (en) * 2015-06-29 2020-06-17 Safran Aircraft Engines Method for manufacturing a blade comprising a squealer tip integrating a small wall
US11814979B1 (en) * 2022-09-21 2023-11-14 Rtx Corporation Systems and methods of hybrid blade tip repair

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