JP5635816B2 - タービンバケット先端シュラウド用の冷却孔出口 - Google Patents
タービンバケット先端シュラウド用の冷却孔出口 Download PDFInfo
- Publication number
- JP5635816B2 JP5635816B2 JP2010137833A JP2010137833A JP5635816B2 JP 5635816 B2 JP5635816 B2 JP 5635816B2 JP 2010137833 A JP2010137833 A JP 2010137833A JP 2010137833 A JP2010137833 A JP 2010137833A JP 5635816 B2 JP5635816 B2 JP 5635816B2
- Authority
- JP
- Japan
- Prior art keywords
- length
- tip shroud
- narrowed
- diameter length
- cooling holes
- 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.)
- Expired - Fee Related
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
- F05D2240/40—Use of a multiplicity of similar components
-
- 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
- F05D2250/30—Arrangement of components
- F05D2250/32—Arrangement of components according to their shape
- F05D2250/323—Arrangement of components according to their shape convergent
-
- 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
- F05D2250/30—Arrangement of components
- F05D2250/32—Arrangement of components according to their shape
- F05D2250/324—Arrangement of components according to their shape divergent
-
- 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
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Description
12 圧縮機
14 燃焼器
16 タービン
18 外部負荷
20 段
22 第一段
24 ノズル
26 バケット
28 第二段
30 ノズル
32 バケット
34 第三段
36 ノズル
38 バケット
40 高温ガス通路
42 プラットフォーム
44 シャンク
46 ダブテール
48 翼形部
50 先端シュラウド
52 先端
54 冷却孔
56 出口
58 直線壁
100 タービンバケット
110 翼形部
120 先端シュラウド
130 先端
140 冷却孔
150 出口
160 一定直径
170 狭小化直径の長さ部
180 拡大化直径の長さ部
190 表面
200 ネック部
210 楕円形形状
220 円形形状
230 円形断面
Claims (10)
- 翼形部(110)と、
前記翼形部(110)の先端(130)上に配置された先端シュラウド(120)と、
前記翼形部(110)及び先端シュラウド(120)を貫通して半径方向に延びる複数の冷却孔(140)と
を備え、
前記複数の冷却孔(140)の1以上が、前記先端シュラウド(120)の周りに狭小化直径の長さ部(170)と、前記先端シュラウド(120)の表面(190)の周りに拡大化直径の長さ部(180)を含み、
前記狭小化直径の長さ部(170)が前記拡大化直径の長さ部(180)に対して半径方向内側の部分に配置され、
前記狭小化直径の長さ部(170)の長さは、前記拡大化直径の長さ部(180)の長さよりも長く、
前記狭小化直径の長さ部(170)の中心軸が前記拡大化直径の長さ部(180)の中心軸と平行に配置され、かつ前記狭小化直径の長さ部(170)の中心軸に対して、該中心軸に垂直な前記拡大化直径の長さ部(180)の断面の中心がオフセットして配置され、
前記複数の冷却孔(140)の複数の出口(150)からの前記空気が、前記先端シュラウド(120)の表面上にフィルム層を形成する、タービンバケット(100)。 - 前記複数の冷却孔(1400)の1以上が、前記狭小化直径の長さ部(170)及び拡大化直径の長さ部(180)間にネック部(200)を含む、請求項1記載のタービンバケット(100)。
- 前記拡大化直径の長さ部(180)がほぼ楕円形形状(210)又は、ほぼ円形形状(230)の断面を含み、
前記狭小化直径の長さ部(170)がほぼ楕円形形状(210)又は、ほぼ円形形状(230)を含む、請求項1または2に記載のタービンバケット(100)。 - 前記複数の冷却孔(140)は、前記先端シュラウド(120)を貫通して延びる複数の出口(56)を備え、
前記複数の出口(56)の各々が、前記タービンバケット(100)を備えるタービン(16)の軸方向の異なる位置に配置される、請求項1乃至3のいずれかに記載のタービンバケット(100)。 - 第二段バケットをさらに含む、請求項1乃至4のいずれかに記載のタービンバケット(100)。
- タービンバケット(100)を冷却する方法であって、
前記タービンバケット(100)を貫通して延びる複数の冷却孔(140)を通して空気を流すステップと、
前記複数の冷却孔(140)内の狭小化直径の長さ部(170)を通して前記空気を流すステップと、
前記複数の冷却孔(140)の複数の出口(150)の周りの拡大化直径の長さ部(180)を通して前記空気を流すステップと、
前記複数の出口(150)からの前記空気により、前記先端シュラウド(120)の表面上にフィルム層を形成するステップと、
を含み、
前記狭小化直径の長さ部(170)が前記拡大化直径の長さ部(180)に対して半径方向内側の部分に配置され、
前記狭小化直径の長さ部(170)が第1の長さを含み、前記拡大化直径の長さ部(180)が第2の長さを含み、前記第1の長さが前記第2の長さよりも大きく、
前記狭小化直径の長さ部(170)の中心軸が前記拡大化直径の長さ部(180)の中心軸と平行かつ前記狭小化直径の長さ部(170)の中心軸に対して、該中心軸に垂直な前記拡大化直径の長さ部(180)の断面の中心がオフセットして配置される、方法。 - 前記狭小化直径の長さ部(170)を通して前記空気を流すステップが、空気の速度を上昇させるステップを含む、請求項6に記載の方法。
- 前記狭小化直径の長さ部(170)を通して前記空気を流すステップが、熱伝達率を高めるステップを含む、請求項6または7に記載の方法。
- 前記タービンバケット(100)が、
翼形部(110)と、
前記翼形部(110)の先端(130)上に配置された先端シュラウド(120)と、
前記翼形部(110)及び先端シュラウド(120)を貫通して半径方向に延びる前記複数の冷却孔(140)と
を備え、
前記先端シュラウド(120)の表面上に再循環流によりもたらされるフィルム層を形成するステップを含む、請求項6乃至8のいずれかに記載の方法。 - 前記拡大化直径の長さ部(180)がほぼ楕円形形状(210)又は、ほぼ円形形状(230)の断面を含み、
前記狭小化直径の長さ部(170)がほぼ楕円形形状(210)又は、ほぼ円形形状(230)を含む、請求項6乃至9のいずれかに記載の方法。
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US12/490,429 | 2009-06-24 | ||
US12/490,429 US8511990B2 (en) | 2009-06-24 | 2009-06-24 | Cooling hole exits for a turbine bucket tip shroud |
Publications (2)
Publication Number | Publication Date |
---|---|
JP2011007181A JP2011007181A (ja) | 2011-01-13 |
JP5635816B2 true JP5635816B2 (ja) | 2014-12-03 |
Family
ID=43218053
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
JP2010137833A Expired - Fee Related JP5635816B2 (ja) | 2009-06-24 | 2010-06-17 | タービンバケット先端シュラウド用の冷却孔出口 |
Country Status (5)
Country | Link |
---|---|
US (1) | US8511990B2 (ja) |
JP (1) | JP5635816B2 (ja) |
CN (1) | CN101929358A (ja) |
CH (1) | CH701304B1 (ja) |
DE (1) | DE102010017363A1 (ja) |
Families Citing this family (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US9051842B2 (en) * | 2012-01-05 | 2015-06-09 | General Electric Company | System and method for cooling turbine blades |
US20140161625A1 (en) * | 2012-12-11 | 2014-06-12 | General Electric Company | Turbine component having cooling passages with varying diameter |
US9644539B2 (en) * | 2013-11-12 | 2017-05-09 | Siemens Energy, Inc. | Cooling air temperature reduction using nozzles |
US9528380B2 (en) * | 2013-12-18 | 2016-12-27 | General Electric Company | Turbine bucket and method for cooling a turbine bucket of a gas turbine engine |
JP6025941B1 (ja) * | 2015-08-25 | 2016-11-16 | 三菱日立パワーシステムズ株式会社 | タービン動翼、及び、ガスタービン |
JP6025940B1 (ja) * | 2015-08-25 | 2016-11-16 | 三菱日立パワーシステムズ株式会社 | タービン動翼、及び、ガスタービン |
US10184342B2 (en) * | 2016-04-14 | 2019-01-22 | General Electric Company | System for cooling seal rails of tip shroud of turbine blade |
US10590786B2 (en) | 2016-05-03 | 2020-03-17 | General Electric Company | System and method for cooling components of a gas turbine engine |
US20180216474A1 (en) * | 2017-02-01 | 2018-08-02 | General Electric Company | Turbomachine Blade Cooling Cavity |
CN110159357B (zh) * | 2019-06-04 | 2021-01-29 | 北京航空航天大学 | 一种提升被动安全的航空发动机涡轮叶片缩扩型供气通道 |
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-
2009
- 2009-06-24 US US12/490,429 patent/US8511990B2/en active Active
-
2010
- 2010-06-14 DE DE102010017363A patent/DE102010017363A1/de not_active Ceased
- 2010-06-17 JP JP2010137833A patent/JP5635816B2/ja not_active Expired - Fee Related
- 2010-06-23 CH CH01008/10A patent/CH701304B1/de not_active IP Right Cessation
- 2010-06-24 CN CN201010220320XA patent/CN101929358A/zh active Pending
Also Published As
Publication number | Publication date |
---|---|
US8511990B2 (en) | 2013-08-20 |
CH701304B1 (de) | 2014-07-15 |
US20100329862A1 (en) | 2010-12-30 |
CN101929358A (zh) | 2010-12-29 |
JP2011007181A (ja) | 2011-01-13 |
CH701304A2 (de) | 2010-12-31 |
DE102010017363A1 (de) | 2010-12-30 |
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