WO2015044007A1 - Anordnung von kühlkanälen in einer turbinenschaufel - Google Patents
Anordnung von kühlkanälen in einer turbinenschaufel Download PDFInfo
- Publication number
- WO2015044007A1 WO2015044007A1 PCT/EP2014/069747 EP2014069747W WO2015044007A1 WO 2015044007 A1 WO2015044007 A1 WO 2015044007A1 EP 2014069747 W EP2014069747 W EP 2014069747W WO 2015044007 A1 WO2015044007 A1 WO 2015044007A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- cooling
- blade
- arrangement
- cooling channels
- turbine blade
- Prior art date
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
- F01D5/14—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
- F01D5/188—Convection cooling with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall
-
- 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
- F05D2220/00—Application
- F05D2220/30—Application in turbines
- F05D2220/32—Application in turbines in gas turbines
-
- 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
- F05D2260/201—Heat transfer, e.g. cooling by impingement of a fluid
-
- 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
- F05D2260/202—Heat transfer, e.g. cooling by film cooling
Definitions
- the invention relates to an arrangement of cooling channels in a turbine blade.
- An arrangement of a plurality of cooling channels, that is to say at least two cooling channels, within a turbine blade for conveying cooling fluid is proposed.
- the cooling fluid is usually air.
- cooling channels are connected to one another at selected locations and are separated from one another in other areas. Due to the connections at selected points, cooling fluid can pass from one cooling channel into another cooling channel. If a leak had occurred in the other cooling channel upstream of the connection, cooling would be lost without the connection downstream. Through the connection, the cooling can be largely maintained downstream of the connection. But it is also necessary to separate the cooling channels in other areas from each other. Without the separation cooling fluid could pass unhindered in the event of a leak to the leak, so that the cooling would in turn be more affected.
- At least one cooling channel begins at the blade root in a region near the inlet ⁇ edge of the turbine blade.
- the inlet for the cooling fluid is, even with the arrangements known in the prior art, for structural reasons regularly at the blade root. Because at the leading edge that drives the turbine blade
- a blade root 2 with which the turbine blade is attached to a rotor.
- On the left is an entrance edge 3 can be seen.
- the leading edge 3 is the area to which a gas mixture driving the turbine blade first impinges.
- Above a blade tip 4 can be seen.
- a trailing edge 5 is arranged.
- the turbine ⁇ blade is not flat, but curved. In this case, the leading edge 3 and the trailing edge 5 may be straight, but also curved.
- the blade 2 and the paddle blade tip go as curved and the rest of the shovel ⁇ area in any case.
- the curvature is due to an aerodynamic shape of the turbine blade.
- the turbine blade has a non-illustrated front wall, which runs trailing edge from the leading edge to the ver ⁇ and extending spaced therefrom rear wall, which leads back from the trailing edge to the leading edge.
- the distance between the front wall and the rear wall in the region of the leading edge 3 and the trailing edge 5 is very low and increases toward the blade center.
- a first cooling channel 6 begins at the blade root 2 and runs directly along the inlet edge 3.
- a further cooling channel 7 extends away from the blade root 2 and is separated from the cooling channel 6.
- the cooling channels 6 and 7 open into a region 8 which is close to the inlet edge 3 and near the blade root 2 is located.
- the cooling ⁇ channels 6 and 7 are interconnected.
- a diagonal channel 9 which leads into a region 10 near the trailing edge 5 and near the blade tip 4, also begins.
- a cooling passage 11 extends parallel to the scene ⁇ felfuß 2.
- the cooling channel 11 opens into a parallel to the off ⁇ takes edge 5 extending cooling channel 12. Following the Diago ⁇ nalkanal 9 from the area 8 near the leading edge 3 for loading ⁇ rich 10 near
- the outlet edge 5 branch off two cooling channels 13 and 14, which run parallel to the cooling channel 11 and open into the cooling channel 12.
Abstract
Description
Claims
Priority Applications (4)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CN201480052859.5A CN105593471A (zh) | 2013-09-25 | 2014-09-17 | 涡轮机叶片内冷却通道的布置 |
EP14772098.1A EP3022397A1 (de) | 2013-09-25 | 2014-09-17 | Anordnung von kühlkanälen in einer turbinenschaufel |
US15/023,392 US20160208622A1 (en) | 2013-09-25 | 2014-09-17 | Arrangement of cooling channels in a turbine blade |
JP2016516886A JP2016533446A (ja) | 2013-09-25 | 2014-09-17 | タービンブレード内の冷却チャネルの配列 |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP13185944.9 | 2013-09-25 | ||
EP13185944.9A EP2853689A1 (de) | 2013-09-25 | 2013-09-25 | Anordnung von Kühlkanälen in einer Turbinenschaufel |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2015044007A1 true WO2015044007A1 (de) | 2015-04-02 |
Family
ID=49303737
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/EP2014/069747 WO2015044007A1 (de) | 2013-09-25 | 2014-09-17 | Anordnung von kühlkanälen in einer turbinenschaufel |
Country Status (5)
Country | Link |
---|---|
US (1) | US20160208622A1 (de) |
EP (2) | EP2853689A1 (de) |
JP (1) | JP2016533446A (de) |
CN (1) | CN105593471A (de) |
WO (1) | WO2015044007A1 (de) |
Families Citing this family (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR3037830B1 (fr) * | 2015-06-29 | 2024-02-16 | Snecma | Ensemble de moulage d'une aube de turbomachine, comprenant une portion en relief de grande section |
US10544684B2 (en) * | 2016-06-29 | 2020-01-28 | General Electric Company | Interior cooling configurations for turbine rotor blades |
FR3057906B1 (fr) * | 2016-10-20 | 2019-03-15 | Safran Aircraft Engines | Aube de turbomachine a refroidissement optimise |
US10422229B2 (en) * | 2017-03-21 | 2019-09-24 | United Technologies Corporation | Airfoil cooling |
US10697301B2 (en) * | 2017-04-07 | 2020-06-30 | General Electric Company | Turbine engine airfoil having a cooling circuit |
US11644046B2 (en) * | 2018-01-05 | 2023-05-09 | Aurora Flight Sciences Corporation | Composite fan blades with integral attachment mechanism |
EP3832069A1 (de) * | 2019-12-06 | 2021-06-09 | Siemens Aktiengesellschaft | Turbinenschaufel für eine stationäre gasturbine |
Citations (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE1097212B (de) * | 1956-10-22 | 1961-01-12 | Her Majesty The Queen In The R | Mit Kuehlkanaelen versehene Schaufel, insbesondere fuer Gasturbinen |
US5536143A (en) * | 1995-03-31 | 1996-07-16 | General Electric Co. | Closed circuit steam cooled bucket |
EP0939196A2 (de) * | 1998-02-26 | 1999-09-01 | Kabushiki Kaisha Toshiba | Gasturbinenschaufel |
US6382914B1 (en) * | 2001-02-23 | 2002-05-07 | General Electric Company | Cooling medium transfer passageways in radial cooled turbine blades |
EP1471210A1 (de) * | 2003-04-24 | 2004-10-27 | Siemens Aktiengesellschaft | Turbinenbauteil mit Prallkühlblech |
US20050084370A1 (en) * | 2003-07-29 | 2005-04-21 | Heinz-Jurgen Gross | Cooled turbine blade |
Family Cites Families (14)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2641439A (en) * | 1947-10-01 | 1953-06-09 | Chrysler Corp | Cooled turbine or compressor blade |
US2687278A (en) * | 1948-05-26 | 1954-08-24 | Chrysler Corp | Article with passages |
GB827289A (en) * | 1955-10-26 | 1960-02-03 | Wiggin & Co Ltd Henry | Improvements relating to hollow turbine or compressor blades |
US3017159A (en) * | 1956-11-23 | 1962-01-16 | Curtiss Wright Corp | Hollow blade construction |
NL228237A (de) * | 1957-06-07 | |||
BE571212A (de) * | 1958-09-10 | |||
US3171631A (en) * | 1962-12-05 | 1965-03-02 | Gen Motors Corp | Turbine blade |
US3554663A (en) * | 1968-09-25 | 1971-01-12 | Gen Motors Corp | Cooled blade |
JPS59231103A (ja) * | 1983-06-14 | 1984-12-25 | Toshiba Corp | ガスタ−ビン冷却翼 |
JPS6285102A (ja) * | 1985-10-11 | 1987-04-18 | Hitachi Ltd | ガスタ−ビン冷却翼 |
JP2851575B2 (ja) * | 1996-01-29 | 1999-01-27 | 三菱重工業株式会社 | 蒸気冷却翼 |
EP2378073A1 (de) * | 2010-04-14 | 2011-10-19 | Siemens Aktiengesellschaft | Lauf- oder Leitschaufel für eine Turbomaschine |
CN201991570U (zh) * | 2011-03-11 | 2011-09-28 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | 燃气轮机的涡轮转子叶片 |
US9528379B2 (en) * | 2013-10-23 | 2016-12-27 | General Electric Company | Turbine bucket having serpentine core |
-
2013
- 2013-09-25 EP EP13185944.9A patent/EP2853689A1/de not_active Withdrawn
-
2014
- 2014-09-17 WO PCT/EP2014/069747 patent/WO2015044007A1/de active Application Filing
- 2014-09-17 EP EP14772098.1A patent/EP3022397A1/de not_active Withdrawn
- 2014-09-17 CN CN201480052859.5A patent/CN105593471A/zh active Pending
- 2014-09-17 JP JP2016516886A patent/JP2016533446A/ja active Pending
- 2014-09-17 US US15/023,392 patent/US20160208622A1/en not_active Abandoned
Patent Citations (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE1097212B (de) * | 1956-10-22 | 1961-01-12 | Her Majesty The Queen In The R | Mit Kuehlkanaelen versehene Schaufel, insbesondere fuer Gasturbinen |
US5536143A (en) * | 1995-03-31 | 1996-07-16 | General Electric Co. | Closed circuit steam cooled bucket |
EP0939196A2 (de) * | 1998-02-26 | 1999-09-01 | Kabushiki Kaisha Toshiba | Gasturbinenschaufel |
US6382914B1 (en) * | 2001-02-23 | 2002-05-07 | General Electric Company | Cooling medium transfer passageways in radial cooled turbine blades |
EP1471210A1 (de) * | 2003-04-24 | 2004-10-27 | Siemens Aktiengesellschaft | Turbinenbauteil mit Prallkühlblech |
US20050084370A1 (en) * | 2003-07-29 | 2005-04-21 | Heinz-Jurgen Gross | Cooled turbine blade |
Also Published As
Publication number | Publication date |
---|---|
EP3022397A1 (de) | 2016-05-25 |
JP2016533446A (ja) | 2016-10-27 |
US20160208622A1 (en) | 2016-07-21 |
CN105593471A (zh) | 2016-05-18 |
EP2853689A1 (de) | 2015-04-01 |
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