JP5270832B2 - 動翼用エアフォイル及びタービン翼 - Google Patents
動翼用エアフォイル及びタービン翼 Download PDFInfo
- Publication number
- JP5270832B2 JP5270832B2 JP2006342783A JP2006342783A JP5270832B2 JP 5270832 B2 JP5270832 B2 JP 5270832B2 JP 2006342783 A JP2006342783 A JP 2006342783A JP 2006342783 A JP2006342783 A JP 2006342783A JP 5270832 B2 JP5270832 B2 JP 5270832B2
- Authority
- JP
- Japan
- Prior art keywords
- trailing edge
- airfoil
- slot
- slots
- length
- 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
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
- F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
- F01D5/186—Film cooling
-
- 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
- F05D2240/10—Stators
- F05D2240/12—Fluid guiding means, e.g. vanes
- F05D2240/122—Fluid guiding means, e.g. vanes related to the trailing edge of a stator vane
-
- 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
- F05D2240/20—Rotors
- F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
- F05D2240/304—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor related to the trailing edge of a rotor blade
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Description
12 低圧圧縮機
14 高圧圧縮機
16 燃焼器
18 高圧タービン
20 低圧タービン
21 第1シャフト
22 第2シャフト
24 排気ノズル
80 高圧タービン翼
81 スロットパターン
82 エアフォイル
84 シャンク
86 前縁
88 後縁
90 圧力側壁
92 吸引側壁
94 エアフォイルの先端
96 末端
98 プラットフォーム
100 ダブテール
102 上部
104 下部
108 スロット
120 隔壁
150 第1スロット
152 第2スロット
154 第3スロット
160 入口
162 入口
164 入口
166 出口
168 出口
170 出口
Claims (5)
- 圧力側壁(90)と;
前縁(86)および後縁(88)において前記圧力側壁と接続された吸引側壁(92)と;
前記後縁から前記圧力側壁に沿って延伸する複数の第1後縁スロット(150)と、複数の第2後縁スロット(152)と、複数の第3後縁スロット(154)と
を含み、
前記複数の第1後縁スロットと前記複数の第2後縁スロットと前記複数の第3後縁スロットの各々が、入口と出口と該入口と出口との間で定まる長さを有し、
前記複数の第2後縁スロットの各々が、前記複数の第1及び第3後縁スロットの各々の長さより長い長さを有するものであり、前記複数の第2及び第3後縁スロットが、交互のパターンに配置されている
ことを特徴とする、動翼(80)用エアフォイル(82)。 - 前記圧力側壁(90)および前記吸引側壁(92)は、末端(96)と先端(94)の間に半径方向に延伸し、前記複数のスロットがさらに、前記後縁(88)の下部(104)内に形成された複数のスロットと、前記後縁の上部(102)内に形成された複数のスロットとを含み、前記後縁の下部(104)内の前記複数のスロットは、前記後縁の上部(102)内の前記複数のスロットと前記翼の末端の間にある、請求項1に記載のエアフォイル(82)。
- 前記複数の第2後縁スロット(152)が、前記後縁の上部(102)内に形成されている、請求項2に記載のエアフォイル(82)。
- 前記複数の第3後縁スロット(154)が、前記後縁の上部(102)内に形成されている、請求項2又は3に記載のエアフォイル(82)。
- プラットフォーム(98)と;
前記プラットフォームから半径方向内側に延伸するダブテール(100)と;
前記プラットフォームから半径方向外側に延伸する、請求項1乃至4のいずれか1項に記載のエアフォイル(82)と
を含む、タービン動翼(80)。
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US11/312,059 US7387492B2 (en) | 2005-12-20 | 2005-12-20 | Methods and apparatus for cooling turbine blade trailing edges |
US11/312,059 | 2005-12-20 |
Publications (3)
Publication Number | Publication Date |
---|---|
JP2007170392A JP2007170392A (ja) | 2007-07-05 |
JP2007170392A5 JP2007170392A5 (ja) | 2010-02-12 |
JP5270832B2 true JP5270832B2 (ja) | 2013-08-21 |
Family
ID=37865649
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
JP2006342783A Expired - Fee Related JP5270832B2 (ja) | 2005-12-20 | 2006-12-20 | 動翼用エアフォイル及びタービン翼 |
Country Status (4)
Country | Link |
---|---|
US (1) | US7387492B2 (ja) |
EP (1) | EP1801350A3 (ja) |
JP (1) | JP5270832B2 (ja) |
CN (1) | CN1987053B (ja) |
Families Citing this family (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1985803A1 (de) * | 2007-04-23 | 2008-10-29 | Siemens Aktiengesellschaft | Verfahren zum Herstellen von beschichteten Turbinenlaufschaufeln |
US7735238B2 (en) * | 2008-07-31 | 2010-06-15 | General Electric Company | Nozzle trailing edge position measurement and marking |
US8172534B2 (en) * | 2009-01-21 | 2012-05-08 | General Electric Company | Turbine blade or vane with improved cooling |
US9133819B2 (en) | 2011-07-18 | 2015-09-15 | Kohana Technologies Inc. | Turbine blades and systems with forward blowing slots |
US9051842B2 (en) | 2012-01-05 | 2015-06-09 | General Electric Company | System and method for cooling turbine blades |
US9995148B2 (en) | 2012-10-04 | 2018-06-12 | General Electric Company | Method and apparatus for cooling gas turbine and rotor blades |
CN103412985B (zh) * | 2013-07-23 | 2016-02-03 | 西北工业大学 | 一种气冷叶片尾缘劈缝参数化设计方法 |
US9732617B2 (en) * | 2013-11-26 | 2017-08-15 | General Electric Company | Cooled airfoil trailing edge and method of cooling the airfoil trailing edge |
CN107429568B (zh) | 2015-03-17 | 2019-11-29 | 西门子能源有限公司 | 用于涡轮发动机中的翼型件的在后缘冷却通道中具有收缩扩张出口槽的内部冷却系统 |
JP6345319B1 (ja) * | 2017-07-07 | 2018-06-20 | 三菱日立パワーシステムズ株式会社 | タービン翼及びガスタービン |
Family Cites Families (18)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB1560683A (en) * | 1972-11-28 | 1980-02-06 | Rolls Royce | Turbine blade |
GB2163218B (en) | 1981-07-07 | 1986-07-16 | Rolls Royce | Cooled vane or blade for a gas turbine engine |
US5378108A (en) * | 1994-03-25 | 1995-01-03 | United Technologies Corporation | Cooled turbine blade |
US5800124A (en) | 1996-04-12 | 1998-09-01 | United Technologies Corporation | Cooled rotor assembly for a turbine engine |
JP3238344B2 (ja) | 1997-02-20 | 2001-12-10 | 三菱重工業株式会社 | ガスタービン静翼 |
JP3411775B2 (ja) | 1997-03-10 | 2003-06-03 | 三菱重工業株式会社 | ガスタービン動翼 |
US6164913A (en) * | 1999-07-26 | 2000-12-26 | General Electric Company | Dust resistant airfoil cooling |
US6234754B1 (en) * | 1999-08-09 | 2001-05-22 | United Technologies Corporation | Coolable airfoil structure |
US6290463B1 (en) | 1999-09-30 | 2001-09-18 | General Electric Company | Slotted impingement cooling of airfoil leading edge |
CA2334071C (en) | 2000-02-23 | 2005-05-24 | Mitsubishi Heavy Industries, Ltd. | Gas turbine moving blade |
US6675582B2 (en) | 2001-05-23 | 2004-01-13 | General Electric Company | Slot cooled combustor line |
US6609891B2 (en) * | 2001-08-30 | 2003-08-26 | General Electric Company | Turbine airfoil for gas turbine engine |
US6612811B2 (en) | 2001-12-12 | 2003-09-02 | General Electric Company | Airfoil for a turbine nozzle of a gas turbine engine and method of making same |
US6551063B1 (en) * | 2001-12-20 | 2003-04-22 | General Electric Company | Foil formed structure for turbine airfoil trailing edge |
US6769865B2 (en) * | 2002-03-22 | 2004-08-03 | General Electric Company | Band cooled turbine nozzle |
US6746209B2 (en) | 2002-05-31 | 2004-06-08 | General Electric Company | Methods and apparatus for cooling gas turbine engine nozzle assemblies |
US7014424B2 (en) * | 2003-04-08 | 2006-03-21 | United Technologies Corporation | Turbine element |
US7165940B2 (en) | 2004-06-10 | 2007-01-23 | General Electric Company | Method and apparatus for cooling gas turbine rotor blades |
-
2005
- 2005-12-20 US US11/312,059 patent/US7387492B2/en not_active Expired - Fee Related
-
2006
- 2006-12-20 EP EP06126639A patent/EP1801350A3/en not_active Withdrawn
- 2006-12-20 CN CN2006100640766A patent/CN1987053B/zh not_active Expired - Fee Related
- 2006-12-20 JP JP2006342783A patent/JP5270832B2/ja not_active Expired - Fee Related
Also Published As
Publication number | Publication date |
---|---|
CN1987053B (zh) | 2013-12-18 |
JP2007170392A (ja) | 2007-07-05 |
EP1801350A2 (en) | 2007-06-27 |
US7387492B2 (en) | 2008-06-17 |
US20070140850A1 (en) | 2007-06-21 |
CN1987053A (zh) | 2007-06-27 |
EP1801350A3 (en) | 2010-12-08 |
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