CN101333941A - Domed tip cap and related method - Google Patents
Domed tip cap and related method Download PDFInfo
- Publication number
- CN101333941A CN101333941A CNA2008101293803A CN200810129380A CN101333941A CN 101333941 A CN101333941 A CN 101333941A CN A2008101293803 A CNA2008101293803 A CN A2008101293803A CN 200810129380 A CN200810129380 A CN 200810129380A CN 101333941 A CN101333941 A CN 101333941A
- Authority
- CN
- China
- Prior art keywords
- tip cap
- wheel blade
- airfoil section
- outer end
- shape
- 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.)
- Pending
Links
Images
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
- F01D5/14—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
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention relates to a dome-shaped tip cap and a related method. 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
Technical field
The present invention relates to turbine technology, more particularly, relate to the cap that is used for turbine vane (bucket) or blade.
Background technique
Traditionally, use tip cap (tip cap) to cover the tip of turbine vane aerofoil profile (airfoil) part, wherein, turbine vane has the cooling circuit of inner complications.These tip caps are made by flat plate stock, and typically or be welded on the radial outer end of airfoil section of wheel blade, perhaps with the airfoil section castingin together.Under arbitrary situation, straight tip cap all suffers heavily stressed when operation.
Summary of the invention
In an exemplary and nonrestrictive embodiment, tip cap insert is suitable for being welded on the radial outer end of wheel blade airfoil section.According to this embodiment, the tip cap that is to say for the dome shape of upset, the direction recessed (just as what seen from the wheel blade outside) that the tip cap is radially inside substantially.
The tip cap also is formed with channel portion, and it is suitable for being placed on the interior inner circular bead of tip cap welding airfoil section thereon.
In another exemplary and nonrestrictive embodiment, the tip cap of dome shape and the airfoil section of wheel blade and other aerofoil profile feature are cast integratedly.
Therefore, in one aspect, the wheel blade that is used for turbine is provided, this wheel blade comprises the dovetail mounting portion, the shank part that is limited by platform at its radial outer end and the airfoil section that extends on this platform outer radial ground, this airfoil section has the radial outer end by the tip cap closure, wherein, in the internal surface of this tip cap and the outer surface or both are configured as and have the nonplanar shape that reduces the stress in the tip cap when using.
In yet another aspect, the wheel blade that is used for turbine is provided, the shank part that this wheel blade comprises the dovetail mounting portion, limited by platform at its radial outer end and at the airfoil section of this platform outer radial ground extension, this airfoil section has the radial outer end by the tip cap closure, wherein, the internal surface of this tip cap is the dome shape of radially inside direction at least; And wherein the tip cap is configured as and has one or more internal ribs (internal rib).
In yet another aspect, provide the method for the stress in the tip cap that reduces turbine vane, this method comprises that the airfoil section of turbine vane has radial outer end; And with tip cap closure radial outer end, this tip cap has the nonplanar shape that reduces the stress in the tip cap when using.
To provide more detailed description in conjunction with the accompanying drawing of following sign now.
Description of drawings
Fig. 1 is the perspective view of traditional turbine vane;
Fig. 2 is the detailed drawing of the tip cap portion of aerofoil profile shown in Fig. 1, and it shows with slightly different angle, so that the tip cap on plane as seen;
Fig. 3 is the planimetric map of the airfoil section shown in Fig. 1 and Fig. 2; The cross section that Fig. 4 is intercepted for the line 4-4 along Fig. 3;
Fig. 5 is the plan view of wheel blade airfoil section, and according to the exemplary and nonrestrictive embodiment of technology disclosed herein, this wheel blade has the tip cap of dome shape;
The partial cross section that Fig. 6 is intercepted for the line 6-6 along Fig. 5;
Fig. 7 is similar to the cross section of Fig. 6 for according to another exemplary and nonrestrictive embodiment, but shows the tip cap with the airfoil section castingin dome shape together of wheel blade; With
Fig. 8 be have to Fig. 6 and Fig. 7 in similar orientation but illustrate cross section according to another kind of tip cap shaped of the present invention.
Component list
Wheel blade 10,110
Shank or shank part 14
Aerofoil profile 18,118,218
Tip cap 20,120,220,320
Flange 22,122
Rib 24,123,124
Internal surface 323
Embodiment
Referring to Fig. 1-4, the conventional inner-cooled wheel blade 10 that is used for turbogenerator comprises installs dovetail 12, shank or shank part 14, the platform 16 on the shank top and the airfoil section or the aerofoil profile 18 of extending radially outwardly from platform.Aerofoil profile 18 ends at tip cap 20 in its outermost end.Illustrated tip cap comprises the flat board that is welded on the airfoil section in Fig. 1-4.More particularly, and as finding best among Fig. 4, straight tip cap 20 is placed on the inner peripheral land or flange 22, and welds thereon according to traditional welding technique.Should understand, straight tip cap can also with this aerofoil profile castingin together, eliminated necessity of welding.Can adopt internal rib 24 (being shown in broken lines) to strengthen the tip cap when needing.
Turn to Fig. 5 and Fig. 6 now, illustrate tip cap according to the exemplary and nonrestrictive embodiment of this invention.For simplicity, in Fig. 5 and Fig. 6, use and refer to common means, prefix 1 is arranged but increase corresponding to label used among Fig. 1 to Fig. 4.Therefore, wheel blade 110 comprises the aerofoil profile 118 that has tip cap 120, and wherein, this tip cap 120 is fastened on the radially outermost end place of aerofoil profile.Tip cap 120 can be described as the dome shape with upset, that is to say, the radially inner direction of tip shade is recessed into (or as seeing from the wheel blade outside).In other words, the tip cap is radially given prominence to into wheel interlobar part.Tip cap 120 forms flange or the edge 26 with periphery, and this flange or edge 26 are placed on the inner circular bead or flange 122 of aerofoil profile 118, and again, weld thereon according to traditional welding technique.
In Fig. 7 among the illustrated exemplary and nonrestrictive embodiment, the tip cap 220 of aerofoil profile 218 and airfoil section castingin together, and the tip cap in the image pattern 6 has the dome of upset or the shape that inwardly concaves like that.
By giving the dome shape of upset for (being the plane) tip cap, can reduce typically relevant flexural stress with straight tip cap.In some situation, the benefit that the stress of dome cap reduces can suffice to show that eliminates the correct of rib welding, and wherein, the rib welding is used for the tip cap is fastened on their aerofoil profiles separately traditionally.Should understand that the curvature of tip cap dome is optimized to regardless of the span that is covered provides the stress to tip cap Zone Full to reduce.In addition, the tip cap of dome shape can be provided with known surface characteristics (as swirler) and strengthens convection current (for example seeing internal rib 122 among Fig. 3 and the internal rib 124 among Fig. 5).
Fig. 8 illustrates another exemplary, nonrestrictive mode of execution, and the tip cap 320 of wheel blade 318 keeps straight on the surface 323 within it curving inwardly on its outer surface 321 herein.Shape also provides required stress to reduce.Therefore, should understand, term " dome shape " intention comprises of being used for wheel blade tip cap internal surface and outer surface or both many shapes (no matter be welded on the airfoil section of wheel blade or with this airfoil section castingin and be in the same place), and these shapes can comprise circle, parabola or be different from traditional flat plate stock and reduce other complicated shape of stress.
The dome shape of tip cap also makes it possible to reduce essential material property and/or material thickness, and perhaps need not to change material composition and the running temperature of the tip cap that can raise.In addition, compare, can cover the opening of broad with the straight design of same material and thickness.
Although the present invention has combined and has currently thought that the most practical and preferred embodiment are described, but should be appreciated that, the invention is not restricted to the disclosed embodiments, and just the opposite, this invention is intended to contain the essence and interior various modifications and the equivalent arrangements of scope that are included in appended claims.
Claims (10)
1. wheel blade (110) that is used for turbine, the shank part (14) that it comprises dovetail mounting portion (12), limited by platform at its radial outer end and at the airfoil section (118) of described platform outer radial ground extension, described airfoil section has the radial outer end by tip cap (120) sealing, wherein, in the internal surface of described tip cap and the outer surface or both are configured as and have the nonplanar shape that reduces the stress in the described tip cap when using.
2. wheel blade according to claim 1 is characterized in that, described nonplanar shape is the shape of the dome shape of radially inside direction.
3. wheel blade according to claim 2 is characterized in that, described tip cap and described airfoil section castingin are together.
4. wheel blade according to claim 1 is characterized in that, described tip cap is welded on the described airfoil section.
5. wheel blade according to claim 4 is characterized in that, described tip cap is configured as and has the channel portion (122) that is placed on the shoulder, and described shoulder is formed in the described airfoil section.
6. wheel blade according to claim 1 is characterized in that, described tip cap is configured as and has one or more internal ribs (123).
7. the method for the stress in the tip cap that reduces turbine vane comprises that the airfoil section (118) to described turbine vane provides radial outer end; With
With the described radial outer end of tip cap closure, described tip cap has the nonplanar shape that reduces the stress in the described tip cap (120) when using.
8. method according to claim 7 is characterized in that, described tip cap (120) is configured as and has one or more internal ribs (123).
9. method according to claim 7 is characterized in that, the internal surface of described tip cap (120) and outer surface are the shapes of the dome shape of radially inside direction.
10. method according to claim 7 is characterized in that, the outer surface of described tip cap (120) is the shape of the dome shape of radially inside direction.
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US11/819,030 US20080317597A1 (en) | 2007-06-25 | 2007-06-25 | Domed tip cap and related method |
US11/819030 | 2007-06-25 |
Publications (1)
Publication Number | Publication Date |
---|---|
CN101333941A true CN101333941A (en) | 2008-12-31 |
Family
ID=40076133
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
CNA2008101293803A Pending CN101333941A (en) | 2007-06-25 | 2008-06-25 | Domed tip cap and related method |
Country Status (4)
Country | Link |
---|---|
US (1) | US20080317597A1 (en) |
JP (1) | JP2009002339A (en) |
CN (1) | CN101333941A (en) |
DE (1) | DE102008002906A1 (en) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN104271886A (en) * | 2012-05-09 | 2015-01-07 | 西门子能量股份有限公司 | Repair method of a turbine blade tip |
Families Citing this family (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US8573949B2 (en) * | 2009-09-30 | 2013-11-05 | General Electric Company | Method and system for focused energy brazing |
FR3037974B1 (en) * | 2015-06-29 | 2017-07-21 | Snecma | METHOD FOR MANUFACTURING A VANE COMPRISING A BATHTUB INTEGRATING A WALL |
US11814979B1 (en) * | 2022-09-21 | 2023-11-14 | Rtx Corporation | Systems and methods of hybrid blade tip repair |
Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US6086328A (en) * | 1998-12-21 | 2000-07-11 | General Electric Company | Tapered tip turbine blade |
US6685434B1 (en) * | 2002-09-17 | 2004-02-03 | General Electric Company | Second stage turbine bucket airfoil |
CN1880727A (en) * | 2005-02-25 | 2006-12-20 | 通用电气公司 | Torque-tuned, integrally-covered bucket and related method |
CN1908380A (en) * | 2005-08-03 | 2007-02-07 | 联合工艺公司 | Turbine blades |
US7175391B2 (en) * | 2004-07-08 | 2007-02-13 | United Technologies Corporation | Turbine blade |
Family Cites Families (26)
Publication number | Priority date | Publication date | Assignee | Title |
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US4020538A (en) * | 1973-04-27 | 1977-05-03 | General Electric Company | Turbomachinery blade tip cap configuration |
US3982851A (en) * | 1975-09-02 | 1976-09-28 | General Electric Company | Tip cap apparatus |
US4214355A (en) * | 1977-12-21 | 1980-07-29 | General Electric Company | Method for repairing a turbomachinery blade tip |
US4247254A (en) * | 1978-12-22 | 1981-01-27 | General Electric Company | Turbomachinery blade with improved tip cap |
US4390320A (en) * | 1980-05-01 | 1983-06-28 | General Electric Company | Tip cap for a rotor blade and method of replacement |
US4589823A (en) * | 1984-04-27 | 1986-05-20 | General Electric Company | Rotor blade tip |
US4802828A (en) * | 1986-12-29 | 1989-02-07 | United Technologies Corporation | Turbine blade having a fused metal-ceramic tip |
US4761116A (en) * | 1987-05-11 | 1988-08-02 | General Electric Company | Turbine blade with tip vent |
US5261789A (en) * | 1992-08-25 | 1993-11-16 | General Electric Company | Tip cooled blade |
US5503527A (en) * | 1994-12-19 | 1996-04-02 | General Electric Company | Turbine blade having tip slot |
US5672261A (en) * | 1996-08-09 | 1997-09-30 | General Electric Company | Method for brazing an end plate within an open body end, and brazed article |
US5733102A (en) * | 1996-12-17 | 1998-03-31 | General Electric Company | Slot cooled blade tip |
US6027306A (en) * | 1997-06-23 | 2000-02-22 | General Electric Company | Turbine blade tip flow discouragers |
US5997251A (en) * | 1997-11-17 | 1999-12-07 | General Electric Company | Ribbed turbine blade tip |
US6179556B1 (en) * | 1999-06-01 | 2001-01-30 | General Electric Company | Turbine blade tip with offset squealer |
US6224337B1 (en) * | 1999-09-17 | 2001-05-01 | General Electric Company | Thermal barrier coated squealer tip cavity |
US6506022B2 (en) * | 2001-04-27 | 2003-01-14 | General Electric Company | Turbine blade having a cooled tip shroud |
US6602052B2 (en) * | 2001-06-20 | 2003-08-05 | Alstom (Switzerland) Ltd | Airfoil tip squealer cooling construction |
US6616410B2 (en) * | 2001-11-01 | 2003-09-09 | General Electric Company | Oxidation resistant and/or abrasion resistant squealer tip and method for casting same |
US6634860B2 (en) * | 2001-12-20 | 2003-10-21 | General Electric Company | Foil formed structure for turbine airfoil tip |
US6991430B2 (en) * | 2003-04-07 | 2006-01-31 | General Electric Company | Turbine blade with recessed squealer tip and shelf |
US7063509B2 (en) * | 2003-09-05 | 2006-06-20 | General Electric Company | Conical tip shroud fillet for a turbine bucket |
US7001151B2 (en) * | 2004-03-02 | 2006-02-21 | General Electric Company | Gas turbine bucket tip cap |
US7137782B2 (en) * | 2004-04-27 | 2006-11-21 | General Electric Company | Turbulator on the underside of a turbine blade tip turn and related method |
US7922455B2 (en) * | 2005-09-19 | 2011-04-12 | General Electric Company | Steam-cooled gas turbine bucker for reduced tip leakage loss |
US7695243B2 (en) * | 2006-07-27 | 2010-04-13 | General Electric Company | Dust hole dome blade |
-
2007
- 2007-06-25 US US11/819,030 patent/US20080317597A1/en not_active Abandoned
-
2008
- 2008-06-17 JP JP2008157347A patent/JP2009002339A/en not_active Withdrawn
- 2008-06-25 CN CNA2008101293803A patent/CN101333941A/en active Pending
- 2008-06-25 DE DE102008002906A patent/DE102008002906A1/en not_active Withdrawn
Patent Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US6086328A (en) * | 1998-12-21 | 2000-07-11 | General Electric Company | Tapered tip turbine blade |
US6685434B1 (en) * | 2002-09-17 | 2004-02-03 | General Electric Company | Second stage turbine bucket airfoil |
US7175391B2 (en) * | 2004-07-08 | 2007-02-13 | United Technologies Corporation | Turbine blade |
CN1880727A (en) * | 2005-02-25 | 2006-12-20 | 通用电气公司 | Torque-tuned, integrally-covered bucket and related method |
CN1908380A (en) * | 2005-08-03 | 2007-02-07 | 联合工艺公司 | Turbine blades |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN104271886A (en) * | 2012-05-09 | 2015-01-07 | 西门子能量股份有限公司 | 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 |
Also Published As
Publication number | Publication date |
---|---|
US20080317597A1 (en) | 2008-12-25 |
DE102008002906A1 (en) | 2009-01-02 |
JP2009002339A (en) | 2009-01-08 |
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Legal Events
Date | Code | Title | Description |
---|---|---|---|
C06 | Publication | ||
PB01 | Publication | ||
C10 | Entry into substantive examination | ||
SE01 | Entry into force of request for substantive examination | ||
C02 | Deemed withdrawal of patent application after publication (patent law 2001) | ||
WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20081231 |