EP1126136A3 - Turbine blade with air cooled tip shroud - Google Patents
Turbine blade with air cooled tip shroud Download PDFInfo
- Publication number
- EP1126136A3 EP1126136A3 EP00810966A EP00810966A EP1126136A3 EP 1126136 A3 EP1126136 A3 EP 1126136A3 EP 00810966 A EP00810966 A EP 00810966A EP 00810966 A EP00810966 A EP 00810966A EP 1126136 A3 EP1126136 A3 EP 1126136A3
- Authority
- EP
- European Patent Office
- Prior art keywords
- turbine blade
- air cooled
- blade
- shroud element
- tip shroud
- 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
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
- F01D5/18—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
- F01D5/12—Blades
- F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
- F01D5/225—Blade-to-blade connections, e.g. for damping vibrations by shrouding
-
- 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
- F05D2240/81—Cooled platforms
-
- 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
- F05D2250/10—Two-dimensional
- F05D2250/14—Two-dimensional elliptical
- F05D2250/141—Two-dimensional elliptical circular
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Luftgekühlte Turbinenschaufel (10), welche an der Schaufelspitze ein sich quer zur Schaufellängsachse erstreckendes Deckbandelement (11) aufweist, wobei im Inneren des Deckbandelementes (11) Hohlräume (16,16',17,17') zur Kühlung vorgesehen sind, welche eingangsseitig mit wenigstens einem durch die Turbinenschaufel (10) zur Schaufelspitze verlaufenden Kühlluftkanal (18) in Verbindung stehen, und ausgangsseitig in den die Turbinenschaufel (10) umgebenden Aussenraum münden, bei der die Hohlräume (16,16',17,17') und das Deckbandelement (11) zur Verringerung des Gewichtes des Deckbandelementes (11) in Form und Abmessung aufeinander abgestimmt. Air-cooled turbine blade (10), which at the blade tip a transverse to the blade longitudinal axis extending shroud element (11), wherein in the interior of the shroud element (11) cavities (16,16 ', 17,17') are provided for cooling, which on the input side with at least one of the turbine blade (10) extending to the blade tip cooling air channel (18) are in communication, and the output side in the turbine blade (10) surrounding outer space, in which the cavities (16,16 ', 17,17') and the shroud element (11) adapted to reduce the weight of the shroud element (11) in shape and dimension.
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE1996377 | 1999-12-28 | ||
DE19963377A DE19963377A1 (en) | 1999-12-28 | 1999-12-28 | Turbine blade with actively cooled cover band element |
Publications (3)
Publication Number | Publication Date |
---|---|
EP1126136A2 EP1126136A2 (en) | 2001-08-22 |
EP1126136A3 true EP1126136A3 (en) | 2004-05-19 |
EP1126136B1 EP1126136B1 (en) | 2006-06-14 |
Family
ID=7934748
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP00810966A Expired - Lifetime EP1126136B1 (en) | 1999-12-28 | 2000-10-19 | Turbine blade with air cooled tip shroud |
Country Status (4)
Country | Link |
---|---|
US (1) | US6464460B2 (en) |
EP (1) | EP1126136B1 (en) |
CN (1) | CN1278018C (en) |
DE (2) | DE19963377A1 (en) |
Families Citing this family (23)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US6869270B2 (en) * | 2002-06-06 | 2005-03-22 | General Electric Company | Turbine blade cover cooling apparatus and method of fabrication |
DE602004003757T2 (en) | 2003-07-23 | 2007-10-11 | Alstom Technology Ltd. | Process for the preparation and method for the production of a turbine blade |
EP1515000B1 (en) * | 2003-09-09 | 2016-03-09 | Alstom Technology Ltd | Blading of a turbomachine with contoured shrouds |
US20060280610A1 (en) * | 2005-06-13 | 2006-12-14 | Heyward John P | Turbine blade and method of fabricating same |
GB2430170B (en) * | 2005-09-15 | 2008-05-07 | Rolls Royce Plc | Method of forming a cast component |
US20070201980A1 (en) * | 2005-10-11 | 2007-08-30 | Honeywell International, Inc. | Method to augment heat transfer using chamfered cylindrical depressions in cast internal cooling passages |
US7686581B2 (en) * | 2006-06-07 | 2010-03-30 | General Electric Company | Serpentine cooling circuit and method for cooling tip shroud |
US7762774B2 (en) * | 2006-12-15 | 2010-07-27 | Siemens Energy, Inc. | Cooling arrangement for a tapered turbine blade |
US7568882B2 (en) * | 2007-01-12 | 2009-08-04 | General Electric Company | Impingement cooled bucket shroud, turbine rotor incorporating the same, and cooling method |
US7946817B2 (en) * | 2008-01-10 | 2011-05-24 | General Electric Company | Turbine blade tip shroud |
US20090180894A1 (en) * | 2008-01-10 | 2009-07-16 | General Electric Company | Turbine blade tip shroud |
US8057177B2 (en) * | 2008-01-10 | 2011-11-15 | General Electric Company | Turbine blade tip shroud |
US7946816B2 (en) * | 2008-01-10 | 2011-05-24 | General Electric Company | Turbine blade tip shroud |
US8322986B2 (en) * | 2008-07-29 | 2012-12-04 | General Electric Company | Rotor blade and method of fabricating the same |
GB0901129D0 (en) * | 2009-01-26 | 2009-03-11 | Rolls Royce Plc | Rotor blade |
CH700686A1 (en) * | 2009-03-30 | 2010-09-30 | Alstom Technology Ltd | Blade for a gas turbine. |
CN102069365B (en) * | 2009-11-25 | 2014-12-10 | 中国江南航天工业集团林泉电机厂 | Method for manufacturing radiator and radiator |
US8444372B2 (en) | 2011-02-07 | 2013-05-21 | General Electric Company | Passive cooling system for a turbomachine |
EP2713009B1 (en) * | 2012-09-26 | 2015-03-11 | Alstom Technology Ltd | Cooling method and system for cooling blades of at least one blade row in a rotary flow machine |
JP6576466B2 (en) * | 2015-04-15 | 2019-09-18 | ローベルト ボツシユ ゲゼルシヤフト ミツト ベシユレンクテル ハフツングRobert Bosch Gmbh | Free tip axial fan assembly |
US10947898B2 (en) | 2017-02-14 | 2021-03-16 | General Electric Company | Undulating tip shroud for use on a turbine blade |
JP6636668B1 (en) * | 2019-03-29 | 2020-01-29 | 三菱重工業株式会社 | High-temperature component, method for manufacturing high-temperature component, and method for adjusting flow rate |
US11255198B1 (en) * | 2021-06-10 | 2022-02-22 | General Electric Company | Tip shroud with exit surface for cooling passages |
Citations (9)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3433015A (en) * | 1965-06-23 | 1969-03-18 | Nasa | Gas turbine combustion apparatus |
JPS5847104A (en) * | 1981-09-11 | 1983-03-18 | Agency Of Ind Science & Technol | Turbine rotor blade in gas turbine |
JPH03194101A (en) * | 1989-12-21 | 1991-08-23 | Toshiba Corp | Gas turbine cooling moving blade |
US5306401A (en) * | 1993-03-15 | 1994-04-26 | Fierkens Richard H J | Method for drilling cooling holes in turbine blades |
JPH0828303A (en) * | 1994-07-11 | 1996-01-30 | Mitsubishi Heavy Ind Ltd | Moving blade of gas turbine |
DE19601819A1 (en) * | 1995-02-23 | 1996-08-29 | Bmw Rolls Royce Gmbh | Turbine blade arrangement with a cooled shroud |
EP0927814A1 (en) * | 1997-06-23 | 1999-07-07 | Mitsubishi Heavy Industries, Ltd. | Tip shroud for cooled blade of gas turbine |
EP0935052A2 (en) * | 1998-02-04 | 1999-08-11 | Mitsubishi Heavy Industries, Ltd. | Gas turbine rotor blade |
EP1013884A2 (en) * | 1998-12-24 | 2000-06-28 | ABB Alstom Power (Schweiz) AG | Turbine blade with actively cooled head platform |
Family Cites Families (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3527544A (en) * | 1968-12-12 | 1970-09-08 | Gen Motors Corp | Cooled blade shroud |
GB1605335A (en) * | 1975-08-23 | 1991-12-18 | Rolls Royce | A rotor blade for a gas turbine engine |
US5197852A (en) * | 1990-05-31 | 1993-03-30 | General Electric Company | Nozzle band overhang cooling |
GB9224241D0 (en) * | 1992-11-19 | 1993-01-06 | Bmw Rolls Royce Gmbh | A turbine blade arrangement |
GB2290833B (en) | 1994-07-02 | 1998-08-05 | Rolls Royce Plc | Turbine blade |
US5482435A (en) | 1994-10-26 | 1996-01-09 | Westinghouse Electric Corporation | Gas turbine blade having a cooled shroud |
US5785496A (en) | 1997-02-24 | 1998-07-28 | Mitsubishi Heavy Industries, Ltd. | Gas turbine rotor |
US6254345B1 (en) * | 1999-09-07 | 2001-07-03 | General Electric Company | Internally cooled blade tip shroud |
-
1999
- 1999-12-28 DE DE19963377A patent/DE19963377A1/en not_active Ceased
-
2000
- 2000-10-19 DE DE50012982T patent/DE50012982D1/en not_active Expired - Lifetime
- 2000-10-19 EP EP00810966A patent/EP1126136B1/en not_active Expired - Lifetime
- 2000-11-30 US US09/725,722 patent/US6464460B2/en not_active Expired - Lifetime
- 2000-12-28 CN CN00137072.3A patent/CN1278018C/en not_active Expired - Fee Related
Patent Citations (9)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3433015A (en) * | 1965-06-23 | 1969-03-18 | Nasa | Gas turbine combustion apparatus |
JPS5847104A (en) * | 1981-09-11 | 1983-03-18 | Agency Of Ind Science & Technol | Turbine rotor blade in gas turbine |
JPH03194101A (en) * | 1989-12-21 | 1991-08-23 | Toshiba Corp | Gas turbine cooling moving blade |
US5306401A (en) * | 1993-03-15 | 1994-04-26 | Fierkens Richard H J | Method for drilling cooling holes in turbine blades |
JPH0828303A (en) * | 1994-07-11 | 1996-01-30 | Mitsubishi Heavy Ind Ltd | Moving blade of gas turbine |
DE19601819A1 (en) * | 1995-02-23 | 1996-08-29 | Bmw Rolls Royce Gmbh | Turbine blade arrangement with a cooled shroud |
EP0927814A1 (en) * | 1997-06-23 | 1999-07-07 | Mitsubishi Heavy Industries, Ltd. | Tip shroud for cooled blade of gas turbine |
EP0935052A2 (en) * | 1998-02-04 | 1999-08-11 | Mitsubishi Heavy Industries, Ltd. | Gas turbine rotor blade |
EP1013884A2 (en) * | 1998-12-24 | 2000-06-28 | ABB Alstom Power (Schweiz) AG | Turbine blade with actively cooled head platform |
Non-Patent Citations (3)
Title |
---|
PATENT ABSTRACTS OF JAPAN vol. 007, no. 128 (M - 220) 3 June 1983 (1983-06-03) * |
PATENT ABSTRACTS OF JAPAN vol. 015, no. 457 (M - 1181) 20 November 1991 (1991-11-20) * |
PATENT ABSTRACTS OF JAPAN vol. 1996, no. 05 31 May 1996 (1996-05-31) * |
Also Published As
Publication number | Publication date |
---|---|
CN1278018C (en) | 2006-10-04 |
CN1301911A (en) | 2001-07-04 |
US6464460B2 (en) | 2002-10-15 |
EP1126136A2 (en) | 2001-08-22 |
DE19963377A1 (en) | 2001-07-12 |
US20010006600A1 (en) | 2001-07-05 |
EP1126136B1 (en) | 2006-06-14 |
DE50012982D1 (en) | 2006-07-27 |
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