US20110081245A1 - Radial seal pin - Google Patents
Radial seal pin Download PDFInfo
- Publication number
- US20110081245A1 US20110081245A1 US12/574,746 US57474609A US2011081245A1 US 20110081245 A1 US20110081245 A1 US 20110081245A1 US 57474609 A US57474609 A US 57474609A US 2011081245 A1 US2011081245 A1 US 2011081245A1
- Authority
- US
- United States
- Prior art keywords
- seal pin
- turbine bucket
- bucket
- shank
- gap
- 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
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
- F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
- F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
- F01D5/3015—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type with side plates
-
- 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
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/005—Sealing means between non relatively rotating elements
Abstract
The present application provides a turbine bucket. The turbine bucket may include a shank, a radial seal pin slot positioned on the shank, and a seal pin positioned within the radial seal pin slot. The seal pin may include a pair of shouldered ends.
Description
- The present application relates generally to gas turbine engines and more particularly relates to a radial seal pin design for preventing leakage between gas turbine buckets.
- Gas turbines generally include a rotor with a number of circumferentially spaced blades or buckets. As is known, the buckets generally include an airfoil, a platform, a shank, a dovetail, and other elements. The dovetail may be positioned about a rotor and secured therein. The airfoils project into a hot combustion gas path produced by a combustor so as to convert the kinetic energy of the gas into rotational mechanical energy.
- A radial seal pin may be used between the shanks of adjacent buckets so as to seal against cross-shank leakage with respect to gas turbines using long shank bucket designs. Generally described, the pin contacts a seal slot face angle under centrifugal load due to rotation and slides towards the side seal rails. The slot face angle forces the pin towards the adjacent bucket so as to prevent cross-shank leakage between two bucket shank cavities.
- Current issues with such radial seal pins include mushrooming or flattened ends due to the use of low creep resistant material, buckling due to inadequate head space, pin binding, pin lockup, and simple pin wear. Moreover, leakage is still an issue even with properly functioning pins. Leakage areas include the shank inside diameter and outside diameter regions. The cross-shank leakage may lower the purge pressure in the bucket shank cavity. Such lower purge pressure may lead to possible hot gas ingestion and subsequent hardware distress.
- There is thus a desire for improved radial seal pin designs for gas turbines. The improved radial seal pin design should adequately prevent or limit cross-shank leakage while being durable and reliable. Such improved sealing should provide improved cooling, increased bucket life, and overall increased system performance and efficiency.
- The present application thus provides a turbine bucket. The turbine bucket may include a shank, a radial seal pin slot positioned on the shank, and a seal pin positioned within the radial seal pin slot. The seal pin may include a pair of shouldered ends.
- The present application further provides a turbine bucket. The turbine bucket may include a shank, a pair of radial seal pin slots positioned on the shank, and a seal pin positioned within each of the radial seal pin slots. The seal pin may include a pair of shouldered ends with a rounded portion and a flat portion.
- These and other features and improvements of the present application will become apparent to one of ordinary skill in the art upon review of the following detailed description when taken in conjunction with the several drawings and the appended claims.
-
FIG. 1 is a schematic view of a gas turbine engine. -
FIG. 2 is a side view of a known rotor bucket. -
FIG. 3 is a perspective view of a seal pin positioned in the radial seal pin slot of a rotor bucket. -
FIGS. 4A and 4B are side views of shank leakage areas using known seal pins. -
FIG. 5 is a perspective view of a radial seal pin slot of a rotor bucket. -
FIG. 6 is an expanded view of the radial seal pin slot with a sealing pin therein as is described herein. -
FIG. 7 is a side plan view of the seal pin ofFIG. 6 . -
FIG. 8 is an expanded view of an end of the seal pin ofFIG. 6 . -
FIG. 9 is a perspective view of the radial seal pin slot ofFIG. 6 . -
FIG. 10 is a further perspective view of the radial seal pin slot ofFIG. 6 . -
FIGS. 11A and 11B are side views of shank leakage areas filled by the seal pin ofFIG. 6 . - Referring now to the drawings, in which like numbers refer to like elements throughout the several views,
FIG. 1 shows a side cross-sectional view of agas turbine engine 10. As is known, thegas turbine engine 10 may include a compressor 12 to compress an incoming flow of air. The compressor 12 delivers the compressed flow of air to a combustor 14. The combustor 14 mixes the compressed flow of air with a compressed flow of fuel and ignites the mixture. (Although only a single combustor 14 is shown, thegas turbine engine 10 may include any number of combustors 14.) The hot combustion gases are in turn delivered to a turbine 16. The hot combustion gases drive the turbine 16 so as to produce mechanical work. The mechanical work produced in the turbine 16 drives the compressor 12 and an external load such as an electrical generator and the like. - The
gas turbine engine 10 may use natural gas, various other types of syngas, and other types of fuels. The gas turbine engine may be a 9FBA heavy duty gas turbine engine offered by General Electric Company of Schenectady, N.Y. Thegas turbine engine 10 may have other configurations and may use other types of components. Other types of gas turbine engines may be used herein. Multiplegas turbine engines 10, other types of turbines, and other types of power generation equipment may be used herein together. -
FIG. 2 shows an example of a knownrotor bucket 18. As is known, therotor bucket 18 may include anairfoil 20 extending from aplatform 22, ashank 24, and adovetail 26. As described above, thedovetail 26 may be positioned about a rotor (not shown) and secured therein for rotation. Theshank 24 may include a leading edge radialseal pin slot 28 and a trailing edge radialseal pin slot 30. Other rotor bucket designs may be used herein. -
FIG. 3 shows the trailing edge radialseal pin slot 30 with a knownseal pin 32 positioned therein. As is shown, theseal pin 32 generally hasrounded ends 33. In this diagram, α is the bucket angle, i.e., the angle of abucket cover plate 34; β is the seal pin angle, i.e., the angle of a seal pockettop face 35; Fc is the centrifugal force due to bucket rotation; Fp is the force normal to the seal pocket top face; Fs is the force along the seal pocket top; and Fr is the resultant frictional force. For effective sealing, Fs should be greater than Fr. Although not shown here, γ is the angle of aseal pocket corner 36. Generally described, the bucket angle α and the seal pocket face angle β accomplish the sideways loading of thepin 32. Specifically, centrifugal force will force thepin 32 against theseal pocket face 35. The angle γ of theseal pocket corner 36 then will force thepin 32 tangentially towards anadjacent bucket 37 so as to fill agap 39 therebetween. -
FIGS. 4A and 4B show theseal pin 32 positioned between therotor bucket 18 and theadjacent bucket 37.FIG. 4A shows an outerdiameter leakage gap 38. The outerdiameter leakage gap 38 may be about equal to the ligament thickness of the top of theseal slots FIG. 4B shows an innerdiameter leakage gap 40. The innerdiameter leakage gap 40 may be about equal to the amount of binding tolerance on theseal pin 32. The binding tolerance generally accounts for different coefficients of thermal expansion between the seal material and the bucket material as well as transient operating conditions. -
FIGS. 5 and 6 show arotor bucket 100 as is described herein. As described above, therotor bucket 100 may include anairfoil 110, aplatform 120, ashank 130, and a dovetail 140. Theshank 130 includes a pair of radialseal pin slots 150. Although only one radialseal pin slot 150 is shown, theshank 130 will include a leading edge and a trailing edge radial seal pin slot. -
FIGS. 6 through 8 show aseal pin 160 as may be described herein. Theseal pin 160 may have a first shoulderedend 170 and a second shoulderedend 180. As is shown, the shouldered ends 170 have a roundedportion 190 and aflat portion 200. The ends 170, 180 may be largely identical. Thepin 160 may be slightly shorter than theseal pin slot 150 so as to provide for thermal growth and avoid pin binding. - The
seal pin 160 may be made out of an Inconel 738 material (a nickel-chromium superalloy) or similar types of material with sufficient bulk creep strength. Thepin 160 may be positioned within theslots 150 in any orientation. Thepin 160 may be used in any stage of the turbine 16 or elsewhere. - As is shown in
FIGS. 9 and 10 , theshank 130 includes the bucket angle α. Theseal pin slot 150 includes a sealpocket top face 210 with the angle β. The combination of angles α and β make theseal pin 160 move forward under centrifugal force. Likewise, theradial pin slot 150 includes an angled corner 250 with the angle γ. The angle γ makes theseal pin 160 move towards theshank 130 of the next bucket when thepin 160 moves sideways. Likewise, as shown inFIGS. 11A and 11B , the use of theshoulders outer diameter gap 38 and theinner diameter gap 40 described above for improved performance. - Generally described, for determinate sealing:
-
Fs≧Fr -
F c sin(α+β)≧μF p -
F c sin(α+β)≧μF c cos(α+β) -
tan(α+β)≧μ -
μ=0.35 -
α+β≧19.3° - Likewise, angle γ should be greater than the frictional angle between the bucket material and the pin material to prevent pin lock up due to thermal growth during transient conditions:
-
Fs≧Fr -
F sin(γ)≧μF p -
F sin(γ)≧μF cos(γ) -
tan(γ)≧μ -
μ=0.35 -
γ≧19.3° - The present application thus provides better sealing between turbine stage buckets. Specifically, the leakage areas about the radial seal pins may be substantially reduced. Improved sealing provides improved efficiency due to low leakage and also may reduce hot gas ingestion and improve component reliability.
- It should be apparent that the foregoing relates only to certain embodiments of the present application and that numerous changes and modifications may be made herein by one of ordinary skill in the art without departing from the general spirit and scope of the invention as defined by the following claims and the equivalents thereof.
Claims (20)
1. A turbine bucket, comprising:
a shank;
a radial seal pin slot positioned on the shank; and
a seal pin positioned within the radial seal pin slot;
the seal pin comprising a pair of shouldered ends.
2. The turbine bucket of claim 1 , wherein the shank comprises a pair of radial seal pin slots.
3. The turbine bucket of claim 1 , wherein the pair of shouldered ends comprises a rounded portion and a flat portion.
4. The turbine bucket of claim 1 , wherein the seal pin comprises a first length, the radial seal pin slot comprises a second length, and wherein the first length is shorter than the second length.
5. The turbine bucket of claim 1 , further comprising a pair of buckets with a gap in between and wherein the seal pin is positioned in the gap.
6. The turbine bucket of claim 5 , wherein the shank comprises a cover plate with a bucket angle α.
7. The turbine bucket of claim 6 , wherein the radial seal pin slot comprises a seal pocket face with a seal pin bucket angle β.
8. The turbine bucket of claim 7 , wherein the radial seal pin slot comprises an angled corner with an angle γ.
9. The turbine bucket of claim 8 , wherein the combination of the angles α, β, and γ and a centrifugal force position the seal pin in the gap.
10. The turbine bucket of claim 1 , wherein the shank comprises an outer diameter gap and an inner diameter gap and wherein the pair of shouldered ends fill the outer diameter gap and the inner diameter gap.
11. The turbine bucket of claim 1 wherein the seal pin comprises a nickel-chromium alloy.
12. A turbine bucket, comprising:
a shank;
a pair of radial seal pin slots positioned on the shank; and
a seal pin positioned within each of the pair of radial seal pin slots;
the seal pin comprising a pair of shouldered ends with a rounded portion and a flat portion.
13. The turbine bucket of claim 12 , wherein each of the seal pins comprises a first length, each of the radial seal pin slots comprise a second length, and wherein the first length is shorter than the second length.
14. The turbine bucket of claim 1 , further comprising a pair of buckets with a gap in between and wherein the seal pins are positioned in the gap.
15. The turbine bucket of claim 14 , wherein the shank comprises a cover plate with a bucket angle α.
16. The turbine bucket of claim 15 , wherein the radial seal pin slots comprise a seal pocket face with a seal pin bucket angle β.
17. The turbine bucket of claim 16 , wherein the radial seal pin slot comprises an angled corner with an angle γ.
18. The turbine bucket of claim 17 , wherein the combination of the angles α, β, and γ and a centrifugal force position the seal pins in the gap.
19. The turbine bucket of claim 12 , wherein the shank comprises an outer diameter gap and an inner diameter gap and wherein the pair of shouldered ends fill the outer diameter gap and the inner diameter gap.
20. The turbine bucket of claim 12 wherein the seal pin comprises a nickel-chromium alloy.
Priority Applications (5)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US12/574,746 US20110081245A1 (en) | 2009-10-07 | 2009-10-07 | Radial seal pin |
CN2010105129650A CN102031998A (en) | 2009-10-07 | 2010-09-29 | Radial seal pin |
DE102010037858A DE102010037858A1 (en) | 2009-10-07 | 2010-09-29 | Radial sealing pin |
JP2010223337A JP2011080465A (en) | 2009-10-07 | 2010-10-01 | Radial seal pin |
CH01619/10A CH701951A2 (en) | 2009-10-07 | 2010-10-04 | Turbine blade with a seal pin in a seal pin slot. |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US12/574,746 US20110081245A1 (en) | 2009-10-07 | 2009-10-07 | Radial seal pin |
Publications (1)
Publication Number | Publication Date |
---|---|
US20110081245A1 true US20110081245A1 (en) | 2011-04-07 |
Family
ID=43734739
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US12/574,746 Abandoned US20110081245A1 (en) | 2009-10-07 | 2009-10-07 | Radial seal pin |
Country Status (5)
Country | Link |
---|---|
US (1) | US20110081245A1 (en) |
JP (1) | JP2011080465A (en) |
CN (1) | CN102031998A (en) |
CH (1) | CH701951A2 (en) |
DE (1) | DE102010037858A1 (en) |
Cited By (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP2540968A3 (en) * | 2011-07-01 | 2013-07-03 | Alstom Technology Ltd | Turbine blade |
DE102014112838A1 (en) | 2013-09-18 | 2015-03-19 | General Electric Company | Systems and methods for providing one or more cooling holes in a slot surface of a turbine blade |
US20150167480A1 (en) * | 2012-06-15 | 2015-06-18 | General Electric Company | Methods and apparatus for sealing a gas turbine engine rotor assembly |
US20160298478A1 (en) * | 2015-04-07 | 2016-10-13 | General Electric Company | Gas turbine bucket shanks with seal pins |
US10851661B2 (en) | 2017-08-01 | 2020-12-01 | General Electric Company | Sealing system for a rotary machine and method of assembling same |
Families Citing this family (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN109386310A (en) * | 2012-06-30 | 2019-02-26 | 通用电气公司 | Turbine blade sealing structure |
Citations (12)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5873702A (en) * | 1997-06-20 | 1999-02-23 | Siemens Westinghouse Power Corporation | Apparatus and method for sealing gas turbine blade roots |
US6086329A (en) * | 1997-03-12 | 2000-07-11 | Mitsubishi Heavy Industries, Ltd. | Seal plate for a gas turbine moving blade |
US6273683B1 (en) * | 1999-02-05 | 2001-08-14 | Siemens Westinghouse Power Corporation | Turbine blade platform seal |
US6579065B2 (en) * | 2001-09-13 | 2003-06-17 | General Electric Co. | Methods and apparatus for limiting fluid flow between adjacent rotor blades |
US6682307B1 (en) * | 1999-05-14 | 2004-01-27 | Siemens Aktiengesellschaft | Sealing system for a rotor of a turbo engine |
US20050095128A1 (en) * | 2003-10-31 | 2005-05-05 | Benjamin Edward D. | Methods and apparatus for cooling gas turbine engine rotor assemblies |
US7090466B2 (en) * | 2004-09-14 | 2006-08-15 | General Electric Company | Methods and apparatus for assembling gas turbine engine rotor assemblies |
US7147440B2 (en) * | 2003-10-31 | 2006-12-12 | General Electric Company | Methods and apparatus for cooling gas turbine engine rotor assemblies |
US20070286734A1 (en) * | 2006-06-13 | 2007-12-13 | General Electric Company | Bucket Vibration Damper System |
US20080008593A1 (en) * | 2006-07-06 | 2008-01-10 | Siemens Power Generation, Inc. | Turbine blade self locking seal plate system |
US20080014094A1 (en) * | 2005-05-12 | 2008-01-17 | General Electrio Company | Coated bucket damper pin |
US7534090B2 (en) * | 2006-06-13 | 2009-05-19 | General Electric Company | Enhanced bucket vibration system |
Family Cites Families (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US7575416B2 (en) * | 2006-05-18 | 2009-08-18 | United Technologies Corporation | Rotor assembly for a rotary machine |
-
2009
- 2009-10-07 US US12/574,746 patent/US20110081245A1/en not_active Abandoned
-
2010
- 2010-09-29 DE DE102010037858A patent/DE102010037858A1/en not_active Withdrawn
- 2010-09-29 CN CN2010105129650A patent/CN102031998A/en active Pending
- 2010-10-01 JP JP2010223337A patent/JP2011080465A/en not_active Withdrawn
- 2010-10-04 CH CH01619/10A patent/CH701951A2/en not_active Application Discontinuation
Patent Citations (12)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US6086329A (en) * | 1997-03-12 | 2000-07-11 | Mitsubishi Heavy Industries, Ltd. | Seal plate for a gas turbine moving blade |
US5873702A (en) * | 1997-06-20 | 1999-02-23 | Siemens Westinghouse Power Corporation | Apparatus and method for sealing gas turbine blade roots |
US6273683B1 (en) * | 1999-02-05 | 2001-08-14 | Siemens Westinghouse Power Corporation | Turbine blade platform seal |
US6682307B1 (en) * | 1999-05-14 | 2004-01-27 | Siemens Aktiengesellschaft | Sealing system for a rotor of a turbo engine |
US6579065B2 (en) * | 2001-09-13 | 2003-06-17 | General Electric Co. | Methods and apparatus for limiting fluid flow between adjacent rotor blades |
US20050095128A1 (en) * | 2003-10-31 | 2005-05-05 | Benjamin Edward D. | Methods and apparatus for cooling gas turbine engine rotor assemblies |
US7147440B2 (en) * | 2003-10-31 | 2006-12-12 | General Electric Company | Methods and apparatus for cooling gas turbine engine rotor assemblies |
US7090466B2 (en) * | 2004-09-14 | 2006-08-15 | General Electric Company | Methods and apparatus for assembling gas turbine engine rotor assemblies |
US20080014094A1 (en) * | 2005-05-12 | 2008-01-17 | General Electrio Company | Coated bucket damper pin |
US20070286734A1 (en) * | 2006-06-13 | 2007-12-13 | General Electric Company | Bucket Vibration Damper System |
US7534090B2 (en) * | 2006-06-13 | 2009-05-19 | General Electric Company | Enhanced bucket vibration system |
US20080008593A1 (en) * | 2006-07-06 | 2008-01-10 | Siemens Power Generation, Inc. | Turbine blade self locking seal plate system |
Cited By (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP2540968A3 (en) * | 2011-07-01 | 2013-07-03 | Alstom Technology Ltd | Turbine blade |
US9316105B2 (en) | 2011-07-01 | 2016-04-19 | Alstom Technology Ltd | Turbine blade |
US20150167480A1 (en) * | 2012-06-15 | 2015-06-18 | General Electric Company | Methods and apparatus for sealing a gas turbine engine rotor assembly |
US9840920B2 (en) * | 2012-06-15 | 2017-12-12 | General Electric Company | Methods and apparatus for sealing a gas turbine engine rotor assembly |
DE102014112838A1 (en) | 2013-09-18 | 2015-03-19 | General Electric Company | Systems and methods for providing one or more cooling holes in a slot surface of a turbine blade |
US20160298478A1 (en) * | 2015-04-07 | 2016-10-13 | General Electric Company | Gas turbine bucket shanks with seal pins |
US9890653B2 (en) * | 2015-04-07 | 2018-02-13 | General Electric Company | Gas turbine bucket shanks with seal pins |
US10851661B2 (en) | 2017-08-01 | 2020-12-01 | General Electric Company | Sealing system for a rotary machine and method of assembling same |
Also Published As
Publication number | Publication date |
---|---|
JP2011080465A (en) | 2011-04-21 |
DE102010037858A1 (en) | 2011-04-14 |
CH701951A2 (en) | 2011-04-15 |
CN102031998A (en) | 2011-04-27 |
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Legal Events
Date | Code | Title | Description |
---|---|---|---|
AS | Assignment |
Owner name: GENERAL ELECTRIC COMPANY, NEW YORK Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:WALUNJ, JALINDAR APPA;HONKOMP, MARK STEVEN;SIGNING DATES FROM 20090909 TO 20090916;REEL/FRAME:023336/0241 |
|
STCB | Information on status: application discontinuation |
Free format text: ABANDONED -- FAILURE TO PAY ISSUE FEE |