US20040213669A1 - Curved bucket aft shank walls for stress reduction - Google Patents
Curved bucket aft shank walls for stress reduction Download PDFInfo
- Publication number
- US20040213669A1 US20040213669A1 US10/420,868 US42086803A US2004213669A1 US 20040213669 A1 US20040213669 A1 US 20040213669A1 US 42086803 A US42086803 A US 42086803A US 2004213669 A1 US2004213669 A1 US 2004213669A1
- Authority
- US
- United States
- Prior art keywords
- shank
- aft
- bucket
- wall
- trailing edge
- 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.)
- Granted
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
- 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
- F01D11/001—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between stator blade and rotor
-
- 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
- F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow blades
-
- 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
- F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
- F01D5/187—Convection cooling
-
- 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
-
- 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
- F05D2240/00—Components
- F05D2240/80—Platforms for stationary or moving blades
-
- 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
- F05D2250/00—Geometry
- F05D2250/70—Shape
- F05D2250/71—Shape curved
- F05D2250/711—Shape curved convex
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Definitions
- This invention relates generally to turbine blades and, specifically, to a design modification in a turbine blade aft shank wall for stress reduction.
- sealing of the turbine bucket or blade is crucial, as parasitic leaks degrade engine performance.
- Seal pins are typically used to reduce leaks between adjacent buckets. It is therefore also imperative that the ends of adjacent shanks join relatively closely from the concave sides to the convex sides of the buckets.
- This invention relieves stress at the root trailing edge of a rotating turbine airfoil while maintaining adequate wall thickness between core cavities and the aft shank wall.
- the invention also maintains mating side surfaces for sealing and leak reduction. More specifically, the invention utilizes a convexly curved aft shank wall that provides additional material between the aft shank wall and the nearest cooling cavity, and that also enables increased overhang of the trailing edge of the airfoil.
- the aft wall is curved from one side of the bucket to the other, so as to allow adjacent edges to align and thus facilitate sealing between adjacent buckets.
- the invention relates to a turbine bucket comprising an airfoil portion and a shank portion with a substantially horizontal platform radially therebetween, the shank portion having a forward shank wall and an aft shank wall; at least the aft shank wall convexly curved from one side of the bucket to an opposite side of the bucket.
- the invention in another aspect, relates to a turbine bucket comprising an airfoil portion and a shank portion with a substantially horizontal platform radially therebetween, the shank portion having a forward shank wall and an aft shank wall; the aft shank wall convexly curved from one side of the bucket to an opposite side of the bucket; wherein the internal cooling circuit includes a plurality of cavities in the shank portion and the airfoil portion and wherein one of the cavities lies adjacent the aft shank wall; and further wherein the airfoil portion includes a leading edge and a trailing edge, the trailing edge overhanging the aft shank wall.
- FIG. 1 is a perspective view of a conventional turbine bucket
- FIG. 2 is an enlarged partial perspective of the bucket shown in FIG. 1, sectioned at a location of minimum wall thickness between an aft core cavity and the aft shank wall of the bucket;
- FIG. 3 is a simplified partial section, in plan, of a pair of conventional buckets shown in side-by-side relationship as installed on a turbine wheel;
- FIG. 4 is a view similar to FIG. 3, but sectioned through the airfoil portions of the buckets;
- FIG. 5 is a partial section in plan of two adjacent buckets, with curved aft shank walls in accordance with an exemplary embodiment of this invention.
- FIG. 6 is a view similar to FIG. 5 but sectioned through the airfoil portions of the buckets.
- FIG. 1 illustrates a conventional turbine bucket 10 that includes generally a shank portion 12 , an attachment portion 14 , a platform portion 16 and an airfoil portion (or simply, “airfoil” 18 ).
- the platform portion 16 is radially between the shank portion 12 and the airfoil portion 18 , with the airfoil portion 18 joined to the upper or radially outer surface of the platform.
- So called “angel wings” or sealing flanges 20 , 22 project axially away from the forward and aft walls 24 , 26 , respectively, of the shank portion 12 .
- the attachment portion 14 is shown to be of the generally “axial entry” type and includes a “firtree” 28 , (the attachment portion could also be in the form of a dovetail or other surface locking configuration) designed to mate with a complementary-shaped groove (not shown) on the periphery of the turbine rotor wheel. It will be understood that the invention described herein is not limited by the configuration of the attachment portion 14 .
- the airfoil portion 18 has a leading edge 30 and a trailing edge 32 , with a concave surface 34 on the pressure side of the airfoil portion.
- the bucket 10 is formed with an internal cooling circuit that includes cooling passages or cavities 36 in the shank portion 12 that communicate with larger inlet and outlet manifolds (not shown) in the shank portion attachment 14 and that extend upwardly into the airfoil portion 18 .
- the cavity 38 that is located adjacent the aft wall 26 .
- FIGS. 2 and 3 illustrate the close proximity of the cavity 38 to the aft shank wall 26 with a relatively thin ligament 48 therebetween.
- FIG. 3 also illustrates the manner in which adjacent buckets 10 and 110 are closely aligned when mounted on a turbine wheel, with respective corner edges 40 , 42 of bucket 10 closely aligned with corner edges 140 , 142 of bucket 110 .
- the space between side surfaces 44 and 144 may be on the order of about 0.040 inch, and as mentioned above, seal pins (not shown) are typically located within this space to prevent leakage between the adjacent buckets. Specifically, there are two seal pins, one oriented horizontally as mentioned above, and the other oriented radially, mating between radial surfaces adjacent to edges 42 and 142 of FIG. 3.
- FIG. 4 is similar to FIG. 3 but also shows the airfoil portions 18 , 118 of the respective buckets 10 , 110 .
- the extent of overhang of the trailing edge 32 relative to the aft shank wall 26 is the extent of overhang of the trailing edge 32 relative to the aft shank wall 26 . It will be appreciated that simply extending the aft wall to increase the width of ligament 48 between cavity 38 and the aft shank wall 26 would impair the ability to have an acceptable overhang.
- the bucket 210 is formed with forward and aft shank walls 224 , 226 .
- the aft shank wall 226 is convexly curved from side to side, i.e., such that the convex surface projects axially relative to the turbine rotor centerline indicated at 46 .
- the trailing edge 232 is afforded considerably more overhang vis-a-vis the aft shank wall 226 than in the prior design (see FIG. 4).
- the corner edges 240 , 242 of the bucket 210 may still correctly align with facing corner edges 340 , 342 of adjacent bucket 310 .
Abstract
A turbine bucket comprising an airfoil portion and a shank portion with a substantially horizontal platform radially therebetween, the shank portion having a forward shank wall and an aft shank wall; at least the aft shank wall convexly curved from one side of the bucket to an opposite side of the bucket.
Description
- This invention relates generally to turbine blades and, specifically, to a design modification in a turbine blade aft shank wall for stress reduction.
- When a bucket in a power systems turbine or a blade in an aircraft engine requires a hollow core for cooling air, the proximity of the core cooling cavities to the forward and rear shank walls (coverplates) can be problematic. For example, the cooling cavity closest to the aft shank wall may create a barely sufficient, thin metal ligament between the aft wall and the cooling cavity, causing a high stress location and potentially low part life. Additionally, this situation may preclude the shank wall from undercutting the airfoil trailing edge, a desired condition for airfoil root trailing edge stress relief. In other words, the desire to have the trailing edge overhang the aft shank wall often competes with the requirement to maintain adequate wall thickness between the core cavity and the aft shank wall.
- Reduction of stress, particularly in the airfoil root trailing edge, requires both thermal management of the part to reduce thermal stress, and a geometry designed to relieve the loading of the airfoil trailing edge.
- In a related matter, sealing of the turbine bucket or blade is crucial, as parasitic leaks degrade engine performance. Seal pins are typically used to reduce leaks between adjacent buckets. It is therefore also imperative that the ends of adjacent shanks join relatively closely from the concave sides to the convex sides of the buckets.
- This invention relieves stress at the root trailing edge of a rotating turbine airfoil while maintaining adequate wall thickness between core cavities and the aft shank wall. The invention also maintains mating side surfaces for sealing and leak reduction. More specifically, the invention utilizes a convexly curved aft shank wall that provides additional material between the aft shank wall and the nearest cooling cavity, and that also enables increased overhang of the trailing edge of the airfoil. The aft wall is curved from one side of the bucket to the other, so as to allow adjacent edges to align and thus facilitate sealing between adjacent buckets.
- It will be appreciated that for some bucket applications, it may be desirable to provide a convexly curved surface on the forward shank wall as well.
- In one aspect, therefore, the invention relates to a turbine bucket comprising an airfoil portion and a shank portion with a substantially horizontal platform radially therebetween, the shank portion having a forward shank wall and an aft shank wall; at least the aft shank wall convexly curved from one side of the bucket to an opposite side of the bucket.
- In another aspect, the invention relates to a turbine bucket comprising an airfoil portion and a shank portion with a substantially horizontal platform radially therebetween, the shank portion having a forward shank wall and an aft shank wall; the aft shank wall convexly curved from one side of the bucket to an opposite side of the bucket; wherein the internal cooling circuit includes a plurality of cavities in the shank portion and the airfoil portion and wherein one of the cavities lies adjacent the aft shank wall; and further wherein the airfoil portion includes a leading edge and a trailing edge, the trailing edge overhanging the aft shank wall.
- The invention will now be described in detail in connection with the drawings identified below.
- FIG. 1 is a perspective view of a conventional turbine bucket;
- FIG. 2 is an enlarged partial perspective of the bucket shown in FIG. 1, sectioned at a location of minimum wall thickness between an aft core cavity and the aft shank wall of the bucket;
- FIG. 3 is a simplified partial section, in plan, of a pair of conventional buckets shown in side-by-side relationship as installed on a turbine wheel;
- FIG. 4 is a view similar to FIG. 3, but sectioned through the airfoil portions of the buckets;
- FIG. 5 is a partial section in plan of two adjacent buckets, with curved aft shank walls in accordance with an exemplary embodiment of this invention; and
- FIG. 6 is a view similar to FIG. 5 but sectioned through the airfoil portions of the buckets.
- FIG. 1 illustrates a
conventional turbine bucket 10 that includes generally ashank portion 12, anattachment portion 14, aplatform portion 16 and an airfoil portion (or simply, “airfoil” 18). In terms of a bucket as mounted on a turbine rotor wheel, theplatform portion 16 is radially between theshank portion 12 and theairfoil portion 18, with theairfoil portion 18 joined to the upper or radially outer surface of the platform. So called “angel wings” or sealingflanges aft walls shank portion 12. Theattachment portion 14 is shown to be of the generally “axial entry” type and includes a “firtree” 28, (the attachment portion could also be in the form of a dovetail or other surface locking configuration) designed to mate with a complementary-shaped groove (not shown) on the periphery of the turbine rotor wheel. It will be understood that the invention described herein is not limited by the configuration of theattachment portion 14. Theairfoil portion 18 has a leadingedge 30 and atrailing edge 32, with aconcave surface 34 on the pressure side of the airfoil portion. - As best seen in FIG. 2, the
bucket 10 is formed with an internal cooling circuit that includes cooling passages orcavities 36 in theshank portion 12 that communicate with larger inlet and outlet manifolds (not shown) in theshank portion attachment 14 and that extend upwardly into theairfoil portion 18. Of particular concern here is thecavity 38 that is located adjacent theaft wall 26. FIGS. 2 and 3 illustrate the close proximity of thecavity 38 to theaft shank wall 26 with a relativelythin ligament 48 therebetween. FIG. 3 also illustrates the manner in whichadjacent buckets respective corner edges bucket 10 closely aligned withcorner edges bucket 110. The space betweenside surfaces edges - FIG. 4 is similar to FIG. 3 but also shows the
airfoil portions respective buckets trailing edge 32 relative to theaft shank wall 26. It will be appreciated that simply extending the aft wall to increase the width ofligament 48 betweencavity 38 and theaft shank wall 26 would impair the ability to have an acceptable overhang. - Turning now to FIG. 5, the
bucket 210, otherwise similar tobuckets aft shank walls aft shank wall 226 is convexly curved from side to side, i.e., such that the convex surface projects axially relative to the turbine rotor centerline indicated at 46. This effectively thickens theligament 248 between theclosest cooling cavity 238 and theaft shank wall 226. In addition, as made apparent in FIG. 6, thetrailing edge 232 is afforded considerably more overhang vis-a-vis theaft shank wall 226 than in the prior design (see FIG. 4). At the same time, thecorner edges bucket 210 may still correctly align with facingcorner edges adjacent bucket 310. - 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 (12)
1. A turbine bucket comprising an airfoil portion and a shank portion with a substantially horizontal platform radially therebetween, said shank portion having a forward shank wall and an aft shank wall; at least said aft shank wall convexly curved from one side of the bucket to an opposite side of the bucket.
2. The turbine bucket of claim 1 wherein said shank portion is formed with one or more angel wings projecting from said aft shank wall, and wherein said aft shank wall is convexly curved in an area below said platform but above an uppermost of said one or more angel wings.
3. The turbine bucket of claim 1 wherein said bucket is formed with internal cooling cavities.
4. The turbine bucket of claim 1 wherein said airfoil portion includes a leading edge and a trailing edge and said aft shank wall lies adjacent said trailing edge.
5. The turbine bucket of claim 3 wherein said internal cooling cavities include a plurality of cavities in said shank portion and said airfoil portion and wherein one of said cavities lies adjacent said aft shank wall.
6. The turbine bucket of claim 1 wherein said airfoil portion includes a leading edge and a trailing edge, and wherein said trailing edge overhangs said aft shank wall.
7. The turbine bucket of claim 2 wherein opposite sides of said bucket are substantially straight.
8. The turbine bucket of claim 3 wherein said airfoil portion includes a leading edge and a trailing edge, and wherein said trailing edge overhangs said aft shank wall.
9. The turbine bucket of claim 2 wherein said shank portion also includes a pair of substantially straight side walls.
10. A turbine bucket comprising an airfoil portion and a shank portion with a substantially horizontal platform radially therebetween, said shank portion having a forward shank wall and an aft shank wall; said aft shank wall convexly curved from one side of the bucket to an opposite side of the bucket; wherein said internal cooling circuit includes a plurality of cavities in said shank portion and said airfoil portion and wherein one of said cavities lies adjacent said aft shank wall; and further wherein said airfoil portion includes a leading edge and a trailing edge, said trailing edge overhanging said aft shank wall.
11. The turbine bucket of claim 10 wherein said shank portion is formed with one or more angel wings projecting from said aft shank wall, and wherein said aft shank wall is convexly curved in an area below said platform but above an uppermost of said one or more angel wings.
12. The turbine bucket of claim 11 wherein said airfoil portion includes a leading edge and a trailing edge, and wherein said trailing edge overhangs said aft shank wall.
Priority Applications (7)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US10/420,868 US6805534B1 (en) | 2003-04-23 | 2003-04-23 | Curved bucket aft shank walls for stress reduction |
RU2005136371/06A RU2342539C2 (en) | 2003-04-23 | 2004-04-20 | Turbine blade with deflected rear root walls to reduce stress (versions) |
EP04760033A EP1618287B1 (en) | 2003-04-23 | 2004-04-20 | Turbine bucket with curved aft shank walls for stress reduction |
DE602004014607T DE602004014607D1 (en) | 2003-04-23 | 2004-04-20 | TURBINE BUCKET WITH CURVED REAR WINDOWS FOR TEMPERING |
JP2006513141A JP2006524301A (en) | 2003-04-23 | 2004-04-20 | Turbine bucket with curved rear shank wall for stress reduction |
PCT/US2004/012107 WO2004094788A1 (en) | 2003-04-23 | 2004-04-20 | Turbine bucket with curved aft shank walls for stress reduction |
TW093111266A TW200506175A (en) | 2003-04-23 | 2004-04-22 | Curved bucket aft shank walls for stress reduction |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US10/420,868 US6805534B1 (en) | 2003-04-23 | 2003-04-23 | Curved bucket aft shank walls for stress reduction |
Publications (2)
Publication Number | Publication Date |
---|---|
US6805534B1 US6805534B1 (en) | 2004-10-19 |
US20040213669A1 true US20040213669A1 (en) | 2004-10-28 |
Family
ID=33131485
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US10/420,868 Expired - Fee Related US6805534B1 (en) | 2003-04-23 | 2003-04-23 | Curved bucket aft shank walls for stress reduction |
Country Status (7)
Country | Link |
---|---|
US (1) | US6805534B1 (en) |
EP (1) | EP1618287B1 (en) |
JP (1) | JP2006524301A (en) |
DE (1) | DE602004014607D1 (en) |
RU (1) | RU2342539C2 (en) |
TW (1) | TW200506175A (en) |
WO (1) | WO2004094788A1 (en) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20070031259A1 (en) * | 2005-08-03 | 2007-02-08 | Dube Bryan P | Turbine blades |
Families Citing this family (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB0427083D0 (en) * | 2004-12-10 | 2005-01-12 | Rolls Royce Plc | Platform mounted components |
US7309212B2 (en) * | 2005-11-21 | 2007-12-18 | General Electric Company | Gas turbine bucket with cooled platform leading edge and method of cooling platform leading edge |
US7416391B2 (en) * | 2006-02-24 | 2008-08-26 | General Electric Company | Bucket platform cooling circuit and method |
US10087762B2 (en) | 2011-07-11 | 2018-10-02 | Hamilton Sundstrand Corporation | Scallop curvature for radial turbine wheel |
US8936439B2 (en) | 2011-07-11 | 2015-01-20 | Hamilton Sundstrand Corporation | Radial turbine backface curvature stress reduction |
US9127561B2 (en) * | 2012-03-01 | 2015-09-08 | General Electric Company | Turbine bucket with contoured internal rib |
US9033669B2 (en) | 2012-06-15 | 2015-05-19 | General Electric Company | Rotating airfoil component with platform having a recessed surface region therein |
Citations (9)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5160242A (en) * | 1991-05-31 | 1992-11-03 | Westinghouse Electric Corp. | Freestanding mixed tuned steam turbine blade |
US5267834A (en) * | 1992-12-30 | 1993-12-07 | General Electric Company | Bucket for the last stage of a steam turbine |
US6099253A (en) * | 1998-01-13 | 2000-08-08 | Mitsubishi Heavy Industries, Inc. | Gas turbine rotor blade |
US6190131B1 (en) * | 1999-08-31 | 2001-02-20 | General Electric Co. | Non-integral balanced coverplate and coverplate centering slot for a turbine |
US6428279B1 (en) * | 2000-12-22 | 2002-08-06 | General Electric Company | Low windage loss, light weight closure bucket design and related method |
US6431833B2 (en) * | 1999-09-24 | 2002-08-13 | General Electric Company | Gas turbine bucket with impingement cooled platform |
US6478540B2 (en) * | 2000-12-19 | 2002-11-12 | General Electric Company | Bucket platform cooling scheme and related method |
US6499950B2 (en) * | 1999-04-01 | 2002-12-31 | Fred Thomas Willett | Cooling circuit for a gas turbine bucket and tip shroud |
US6506022B2 (en) * | 2001-04-27 | 2003-01-14 | General Electric Company | Turbine blade having a cooled tip shroud |
Family Cites Families (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB1151937A (en) * | 1966-08-26 | 1969-05-14 | Mini Of Technology | Bladed Rotors for Fluid Flow Machines |
GB1350471A (en) * | 1971-05-06 | 1974-04-18 | Secr Defence | Gas turbine engine |
JP2961065B2 (en) * | 1995-03-17 | 1999-10-12 | 三菱重工業株式会社 | Gas turbine blade |
-
2003
- 2003-04-23 US US10/420,868 patent/US6805534B1/en not_active Expired - Fee Related
-
2004
- 2004-04-20 DE DE602004014607T patent/DE602004014607D1/en not_active Expired - Fee Related
- 2004-04-20 RU RU2005136371/06A patent/RU2342539C2/en active
- 2004-04-20 EP EP04760033A patent/EP1618287B1/en not_active Expired - Lifetime
- 2004-04-20 JP JP2006513141A patent/JP2006524301A/en not_active Ceased
- 2004-04-20 WO PCT/US2004/012107 patent/WO2004094788A1/en active Application Filing
- 2004-04-22 TW TW093111266A patent/TW200506175A/en unknown
Patent Citations (9)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5160242A (en) * | 1991-05-31 | 1992-11-03 | Westinghouse Electric Corp. | Freestanding mixed tuned steam turbine blade |
US5267834A (en) * | 1992-12-30 | 1993-12-07 | General Electric Company | Bucket for the last stage of a steam turbine |
US6099253A (en) * | 1998-01-13 | 2000-08-08 | Mitsubishi Heavy Industries, Inc. | Gas turbine rotor blade |
US6499950B2 (en) * | 1999-04-01 | 2002-12-31 | Fred Thomas Willett | Cooling circuit for a gas turbine bucket and tip shroud |
US6190131B1 (en) * | 1999-08-31 | 2001-02-20 | General Electric Co. | Non-integral balanced coverplate and coverplate centering slot for a turbine |
US6431833B2 (en) * | 1999-09-24 | 2002-08-13 | General Electric Company | Gas turbine bucket with impingement cooled platform |
US6478540B2 (en) * | 2000-12-19 | 2002-11-12 | General Electric Company | Bucket platform cooling scheme and related method |
US6428279B1 (en) * | 2000-12-22 | 2002-08-06 | General Electric Company | Low windage loss, light weight closure bucket design and related method |
US6506022B2 (en) * | 2001-04-27 | 2003-01-14 | General Electric Company | Turbine blade having a cooled tip shroud |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20070031259A1 (en) * | 2005-08-03 | 2007-02-08 | Dube Bryan P | Turbine blades |
US7549846B2 (en) | 2005-08-03 | 2009-06-23 | United Technologies Corporation | Turbine blades |
Also Published As
Publication number | Publication date |
---|---|
EP1618287B1 (en) | 2008-06-25 |
US6805534B1 (en) | 2004-10-19 |
WO2004094788A1 (en) | 2004-11-04 |
TW200506175A (en) | 2005-02-16 |
RU2005136371A (en) | 2006-03-20 |
EP1618287A1 (en) | 2006-01-25 |
RU2342539C2 (en) | 2008-12-27 |
JP2006524301A (en) | 2006-10-26 |
DE602004014607D1 (en) | 2008-08-07 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
US7322796B2 (en) | Turbine vane construction | |
US7090466B2 (en) | Methods and apparatus for assembling gas turbine engine rotor assemblies | |
US6506022B2 (en) | Turbine blade having a cooled tip shroud | |
US5261789A (en) | Tip cooled blade | |
EP1762702B1 (en) | Turbine blade | |
EP1605137B1 (en) | Cooled rotor blade | |
US8961134B2 (en) | Turbine blade or vane with separate endwall | |
US7581924B2 (en) | Turbine vanes with airfoil-proximate cooling seam | |
EP2809885B1 (en) | Rotary fan blade and corresponding assembly | |
EP1507066B1 (en) | Center-located cutter teeth on shrouded turbine blades | |
EP1764481A2 (en) | Stator vane with ceramic airfoil and metallic platforms | |
US20080124214A1 (en) | Turbine outer air seal | |
US20090208339A1 (en) | Blade root stress relief | |
US10941671B2 (en) | Gas turbine engine component incorporating a seal slot | |
US7399163B2 (en) | Rotor blade for a compressor or a gas turbine | |
US6805534B1 (en) | Curved bucket aft shank walls for stress reduction | |
US20080145227A1 (en) | Methods and apparatus for load transfer in rotor assemblies | |
US20070237627A1 (en) | Offset blade tip chord sealing system and method for rotary machines | |
US10822976B2 (en) | Nozzle insert rib cap | |
CN114585802A (en) | Turbine blade, method of manufacturing a turbine blade and method of refurbishing a turbine blade | |
EP3677750B1 (en) | Gas turbine engine component with a trailing edge discharge slot | |
EP0949404A1 (en) | Segmented cascade made from individual vanes which are bolted together |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
AS | Assignment |
Owner name: GENERAL ELECTRIC COMPANY, NEW YORK Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNOR:BRITTINGHAM, ROBERT ALAN;REEL/FRAME:014004/0591 Effective date: 20030422 |
|
FEPP | Fee payment procedure |
Free format text: PAYOR NUMBER ASSIGNED (ORIGINAL EVENT CODE: ASPN); ENTITY STATUS OF PATENT OWNER: LARGE ENTITY |
|
REMI | Maintenance fee reminder mailed | ||
LAPS | Lapse for failure to pay maintenance fees | ||
STCH | Information on status: patent discontinuation |
Free format text: PATENT EXPIRED DUE TO NONPAYMENT OF MAINTENANCE FEES UNDER 37 CFR 1.362 |
|
FP | Lapsed due to failure to pay maintenance fee |
Effective date: 20081019 |