CN102713160A - 内部通风叶片 - Google Patents
内部通风叶片 Download PDFInfo
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- CN102713160A CN102713160A CN2010800602684A CN201080060268A CN102713160A CN 102713160 A CN102713160 A CN 102713160A CN 2010800602684 A CN2010800602684 A CN 2010800602684A CN 201080060268 A CN201080060268 A CN 201080060268A CN 102713160 A CN102713160 A CN 102713160A
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- China
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- blade
- trailing edge
- cavity
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- 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.)
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Classifications
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- 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
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- 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
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- 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
-
- 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
- F05D2260/60—Fluid transfer
- F05D2260/607—Preventing clogging or obstruction of flow paths by dirt, dust, or foreign particles
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Building Environments (AREA)
Abstract
本发明涉及一种叶片,例如高压涡轮叶片,这种叶片被设计为具有最靠近后缘(7)的内部隔离物(9),内部隔离物的上部(20)倾斜地朝向所述后缘,通过在顶部(11)产生新的开(14’)或通过移动从第二空腔开始并朝向后缘区域中的拱腹的小孔(12),以促进冷却气体在后缘的刺孔(15)区域的通风,一般来讲,叶片上角的通风。
Description
技术领域
本发明涉及一种内部通风叶片。
背景技术
涡轮机的叶片通常受到非常高的温度作用,可以与采用气体通风的冷却装置装配在一起,所述冷却装置采用诸如从压缩机区域中的主气流中吸入的相对冷的气体之类的气体,然后,这些气体流动到叶片内部的中空空腔,通过特别出现在拱腹和后缘上的刺孔从空腔中脱离,在拱腹和后缘处的外部低压有助于气流流动。这些设备现在处于试制和测试阶段,通常已经给出了令人满意的结果,但是,由于某些特别困难的条件(例如,在高温涡轮叶片的情况下,叶片受到最高温度的作用)或叶片中的某些特定区域,发现通风不足,此时,仍然需要进行改进。法国专利2 833 294和2 834 015描述了后缘通风技术。
在某些叶片的顶部,具体来讲在后缘和外缘之间的角上,已经观察到冷却故障,这种冷却故障会导致非常高的温度以及某些类型的损坏(例如燃烧)。本发明的目的是解决这个特定的问题。
发明内容
在最通常的形式下,本发明涉及一种叶片,该叶片包括其中可以流动冷却气体的内部空腔,其中,这些空腔由隔离物隔开,其中这些隔离物中距叶片后缘最近的那个隔离物在所测得的叶片距平台的至少70%高度处至叶片的外缘半径的顶部处以更大的倾斜度朝向后缘(由于下文将给出的原因,这种措施通过改善后缘的通风而改进了叶片的角的冷却),所述叶片的特征在于,所述距叶片后缘最近的隔离物所限定的朝向叶片后缘的空腔中的一个空腔包括一系列朝向叶片横向表面的刺孔,其中,所述刺孔通过在平行于所述隔离物的一条线上形成的小孔而出现在所述空腔中。从而,此次通过改善横向表面(拱腹或拱背)的通风,这种改进改善了对叶片的角的冷却。
附图说明
结合附图,通过所示的实施例,以更多的细节对本发明进行说明,其中:
图1和图2是根据本发明的叶片的总体图;
图3示出了本发明所改进的现有设计的细节;以及
图4是根据本发明的设计的相应细节。
具体实施方式
图1和图2示出了叶片(1),叶片(1)附接到容纳在盘(图中未示出)中并与平台(3)配合的根部(2)上。叶片(1)是中空的,并刺有多个空腔(4),这些空腔彼此被在基本上沿径向从根部(2)延伸到叶片(1)的顶部(11)的隔离物(5)所隔开。在其他的空腔中,在距叶片(1)的后缘(7)最近的空腔(6)、邻近空腔(6)的空腔(8)以及隔开空腔(6)与空腔(8)的隔离物(9)之间进行区分,隔离物(9)是距后缘(7)最近的隔离物。
通风气体从叶片(1)所隶属于的机器的另一区域通过根部(2)的区域(10)到达这些空腔(4)(以及(6)和(8)),并上升到叶片(1)的顶部(11);通风气体通过出现在叶片(1)的拱腹(13)和/或拱背(22)上的刺孔(12)逐渐离开这些空腔,而其他的刺孔(14)(在图3和图4中有表示)出现在顶部(11)上,通风气体最后通过其他的刺孔(15)只从出现在后缘(7)上的空腔(6)脱离。
由于刺孔(14)位于空腔(4)的端部,同时还由于通风气体流速较低压力较小,叶片(1)的顶部(11)的通风较困难;由于顶部(11)由在叶片的拱背侧和拱腹侧上延伸的薄的外侧背脊(16)构成,从而形成了被称为“盆”(17)的中空空腔,这产生了另一个不利的因素。背脊(16)使得热气体在叶片的顶部和对着背脊而被限制的箱体之间向外流出,而且背脊(16)当叶片在热膨胀和离心力的组合作用下延伸并碰到对着它的箱体时是受到磨损和撕拉的区域。盆(17)和背脊(16)是难以冷却的区域,在邻近叶片(1)的上角(18)处情况特别严重,在上角(18)处,空腔(6)最狭窄。
应当参照图3。在惯常设计中,为了简化叶片生产,邻近距后缘(7)最近的隔离物(此处以9’标示)与其他的隔离物一样都是直线的,在方向上通常是完全径向的。发明人观察到,在隔离物(9’)和盆(17)底部的壁连接的点处存在低速再流通区域。这个位置处的通风气体的动压力低,使得产生的对顶部(11)通风的上部刺孔无效,使得盆(17)的边缘根本就没有通风,同时还观察到,朝向最邻近顶部(11)的后缘(7)的刺孔(15),通常是三个或四个这种最近的穿透,由于气流压力较低而受到特别低的流速作用。
在图4中可以看到,本发明特有的改进在于,使距后缘(7)最近的隔离物(9)一个上端(20),上端(20)比隔离物(9)的其他部分以更大的倾斜度朝向后缘(7),有利地,上端(20)以修圆形状不断地加大倾斜度,而且以几乎直角连接到盆(17)底部的壁上。上端部分开始于叶片(1)的自平台(3)测量的80%高度处,也可以是70%高度处,直到外边缘,即,盆(17)底部的壁处。其他的隔离物保持直线。技术效果如下:低速直线再流通区域(19)消失,改善了使通风气体到邻近顶部(11)的刺孔(15)的导引,并增大了通风气体的压力,从而还增大了通过这些上部刺孔(15)的流速;从第二空腔(8)朝向拱腹(13)(或拱背)的刺孔(12)可以向后缘(7)移动,其中,第二空腔(8)中的小孔(21)排成一条平行于上部(20)的线;由于第二空腔(8)在顶部被加宽(其中,由于更大的通风难度,在本文所示以及现有设计中的第一空腔(6)通常在顶部并不具有刺孔(12)和(14)),可以包括另一个其他的顶部刺孔(14’)。所有这些改进的效果是,在后缘(7)中通过刺孔(15),在横向拱腹(13)和拱背面上通过移动的刺孔(12),以及在盆(17)中通过附加的顶部刺孔或多个顶部刺孔(14’),叶片(1)的上角(18)被更好地通风和冷却。
Claims (2)
1.一种叶片,其包括用于冷却气体流通的内部空腔(4,6,8),这些空腔被隔离物(5,9)隔开,这些隔离物中距所述叶片的后缘(7)最近的隔离物(9)从所测得的叶片距平台的至少70%高度处至叶片的外缘半径的顶部处以更大的倾斜度朝向外缘半径,所述叶片的特征在于,空腔(8)的被所述距叶片后缘最近的隔离物(9)限定在叶片的后缘区域中的一个空腔包括一系列朝向叶片横向平面的刺孔,所述刺孔通过布置在平行于所述隔离物(9)的线上的小孔(21)而出现在所述空腔(8)中。
2.根据权利要求1所述的叶片,其特征在于,所述更大的倾斜度逐渐变小。
Applications Claiming Priority (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR0959698A FR2954798B1 (fr) | 2009-12-31 | 2009-12-31 | Aube a ventilation interieure |
FR0959698 | 2009-12-31 | ||
PCT/EP2010/070933 WO2011080319A1 (fr) | 2009-12-31 | 2010-12-30 | Aube a ventilation interieure |
Publications (2)
Publication Number | Publication Date |
---|---|
CN102713160A true CN102713160A (zh) | 2012-10-03 |
CN102713160B CN102713160B (zh) | 2016-05-18 |
Family
ID=42133483
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
CN201080060268.4A Active CN102713160B (zh) | 2009-12-31 | 2010-12-30 | 内部通风叶片 |
Country Status (9)
Country | Link |
---|---|
US (1) | US20120282110A1 (zh) |
EP (1) | EP2519713B1 (zh) |
JP (1) | JP5661798B2 (zh) |
CN (1) | CN102713160B (zh) |
BR (1) | BR112012015844A2 (zh) |
CA (1) | CA2785377C (zh) |
FR (1) | FR2954798B1 (zh) |
RU (1) | RU2554397C2 (zh) |
WO (1) | WO2011080319A1 (zh) |
Families Citing this family (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20150361798A1 (en) * | 2013-02-12 | 2015-12-17 | United Technologies Corporation | Fan blade including external cavities |
US9771816B2 (en) * | 2014-05-07 | 2017-09-26 | General Electric Company | Blade cooling circuit feed duct, exhaust duct, and related cooling structure |
JP6353131B1 (ja) | 2017-06-29 | 2018-07-04 | 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 |
Citations (15)
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US3885609A (en) * | 1972-01-18 | 1975-05-27 | Oskar Frei | Cooled rotor blade for a gas turbine |
US4173120A (en) * | 1977-09-09 | 1979-11-06 | International Harvester Company | Turbine nozzle and rotor cooling systems |
EP0034961A1 (fr) * | 1980-02-19 | 1981-09-02 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." | Perfectionnement aux aubes de turbines refroidies |
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US4515526A (en) * | 1981-12-28 | 1985-05-07 | United Technologies Corporation | Coolable airfoil for a rotary machine |
US4604031A (en) * | 1984-10-04 | 1986-08-05 | Rolls-Royce Limited | Hollow fluid cooled turbine blades |
DE4443696A1 (de) * | 1994-12-08 | 1996-06-13 | Abb Management Ag | Gekühlte Turbinenschaufel |
CN1408988A (zh) * | 2001-09-27 | 2003-04-09 | 通用电气公司 | 带倾斜叶尖平台的叶片 |
US20030156943A1 (en) * | 2000-06-21 | 2003-08-21 | Michael Strassberger | Configuration of a coolable turbine blade |
EP1437483A1 (en) * | 2003-01-13 | 2004-07-14 | United Technologies Corporation | Trailing edge cooling of a turbine airfoil |
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EP1918522A2 (en) * | 2006-10-23 | 2008-05-07 | United Technologies Corporation | Turbine component |
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2009
- 2009-12-31 FR FR0959698A patent/FR2954798B1/fr not_active Expired - Fee Related
-
2010
- 2010-12-30 BR BR112012015844A patent/BR112012015844A2/pt not_active IP Right Cessation
- 2010-12-30 EP EP10798151.6A patent/EP2519713B1/fr active Active
- 2010-12-30 RU RU2012132632/06A patent/RU2554397C2/ru active
- 2010-12-30 JP JP2012546450A patent/JP5661798B2/ja active Active
- 2010-12-30 WO PCT/EP2010/070933 patent/WO2011080319A1/fr active Application Filing
- 2010-12-30 CA CA2785377A patent/CA2785377C/fr active Active
- 2010-12-30 CN CN201080060268.4A patent/CN102713160B/zh active Active
- 2010-12-30 US US13/519,339 patent/US20120282110A1/en not_active Abandoned
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US3885609A (en) * | 1972-01-18 | 1975-05-27 | Oskar Frei | Cooled rotor blade for a gas turbine |
US4173120A (en) * | 1977-09-09 | 1979-11-06 | International Harvester Company | Turbine nozzle and rotor cooling systems |
US4416585A (en) * | 1980-01-17 | 1983-11-22 | Pratt & Whitney Aircraft Of Canada Limited | Blade cooling for gas turbine engine |
EP0034961A1 (fr) * | 1980-02-19 | 1981-09-02 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." | Perfectionnement aux aubes de turbines refroidies |
US4515526A (en) * | 1981-12-28 | 1985-05-07 | United Technologies Corporation | Coolable airfoil for a rotary machine |
US4604031A (en) * | 1984-10-04 | 1986-08-05 | Rolls-Royce Limited | Hollow fluid cooled turbine blades |
DE4443696A1 (de) * | 1994-12-08 | 1996-06-13 | Abb Management Ag | Gekühlte Turbinenschaufel |
US20030156943A1 (en) * | 2000-06-21 | 2003-08-21 | Michael Strassberger | Configuration of a coolable turbine blade |
CN1408988A (zh) * | 2001-09-27 | 2003-04-09 | 通用电气公司 | 带倾斜叶尖平台的叶片 |
EP1437483A1 (en) * | 2003-01-13 | 2004-07-14 | United Technologies Corporation | Trailing edge cooling of a turbine airfoil |
CN1536200A (zh) * | 2003-04-08 | 2004-10-13 | ���չ�˾ | 涡轮元件 |
CN1629449A (zh) * | 2003-12-16 | 2005-06-22 | 通用电气公司 | 涡轮叶片的经频率调节的销组 |
US20060013688A1 (en) * | 2004-07-15 | 2006-01-19 | Papple Michael L C | Internally cooled turbine blade |
CN101512106A (zh) * | 2006-09-04 | 2009-08-19 | 西门子公司 | 冷却式涡轮机工作叶片 |
EP1918522A2 (en) * | 2006-10-23 | 2008-05-07 | United Technologies Corporation | Turbine component |
Also Published As
Publication number | Publication date |
---|---|
CN102713160B (zh) | 2016-05-18 |
JP5661798B2 (ja) | 2015-01-28 |
RU2554397C2 (ru) | 2015-06-27 |
JP2013516563A (ja) | 2013-05-13 |
CA2785377A1 (fr) | 2011-07-07 |
RU2012132632A (ru) | 2014-02-10 |
EP2519713B1 (fr) | 2013-11-06 |
WO2011080319A1 (fr) | 2011-07-07 |
US20120282110A1 (en) | 2012-11-08 |
FR2954798B1 (fr) | 2012-03-30 |
CA2785377C (fr) | 2017-02-21 |
FR2954798A1 (fr) | 2011-07-01 |
EP2519713A1 (fr) | 2012-11-07 |
BR112012015844A2 (pt) | 2019-09-24 |
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