CN1169175A - 燃气轮机叶片 - Google Patents
燃气轮机叶片 Download PDFInfo
- Publication number
- CN1169175A CN1169175A CN96191546A CN96191546A CN1169175A CN 1169175 A CN1169175 A CN 1169175A CN 96191546 A CN96191546 A CN 96191546A CN 96191546 A CN96191546 A CN 96191546A CN 1169175 A CN1169175 A CN 1169175A
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- Prior art keywords
- cooling hole
- cooling
- blade
- shower nozzle
- gas turbine
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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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- 238000001816 cooling Methods 0.000 claims abstract description 95
- 238000011144 upstream manufacturing Methods 0.000 claims description 14
- 230000000694 effects Effects 0.000 abstract description 11
- 230000007547 defect Effects 0.000 abstract 1
- 239000007789 gas Substances 0.000 description 11
- 239000002737 fuel gas Substances 0.000 description 4
- 239000000567 combustion gas Substances 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 238000004080 punching Methods 0.000 description 2
- 101100433727 Caenorhabditis elegans got-1.2 gene Proteins 0.000 description 1
- 230000000052 comparative effect Effects 0.000 description 1
- 239000002826 coolant Substances 0.000 description 1
- 230000007423 decrease Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000001771 impaired effect Effects 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 239000007921 spray Substances 0.000 description 1
- 238000005507 spraying Methods 0.000 description 1
Images
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
- F01D5/186—Film 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
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/12—Cooling of plants
- F02C7/16—Cooling of plants characterised by cooling medium
- F02C7/18—Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
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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
- F05D2260/00—Function
- F05D2260/20—Heat transfer, e.g. cooling
- F05D2260/202—Heat transfer, e.g. cooling by film cooling
Abstract
为克服现有燃气轮机叶片喷头冷却孔从叶尖到轮毂直线排列造成的各个孔处压力不均、旋流不均、因而冷却效果不均的缺点,冷却孔被设计成适应燃烧器旋流器的旋转方向的排列形式。在右旋方向下,从气流上游看,叶片前缘叶尖处的冷却孔比轮毂处的冷却孔更靠左;而在左旋情况下,从气流上游看,叶片前缘叶尖处的冷却孔比轮毂处的冷却孔更靠右。这样可在每个冷却孔处达到压力、流场以及冷却效果的均一。
Description
本发明涉及具有喷头冷却机构的燃气轮机叶片。
薄膜冷却,对于高温燃气轮机叶片,成为现今不可缺少的技术。由图3与图4来说明现有的这种技术。图3是空冷叶片剖视图;图4是表示喷头冷却孔配置的斜视图。
一般在高温燃气轮机叶片上,如图3所示,在其前端缘设有喷头冷却孔SC;在叶背上游侧与叶凹下游侧设有薄膜冷却孔FC;丙在其端缘设有叶梢(ピンフィソ)冷却孔PC。
其中喷头冷却孔SC,如图4所示,在叶片2的前端缘、从叶尖一侧TS至轮毂一侧HS成直线排列,几何上向着燃气流动的方向打孔。
喷头冷却与薄膜冷却,是通过向燃气过流面喷以冷却空气,覆盖叶面来提高冷却效率的方法。
但是,若喷出的冷却空气过强,冷却空气会从叶面剥离,而与主流燃气相混合,不能发挥薄膜冷却的本来效果;而若喷出的冷却空气太弱,由于冷却空气流量不足,也不能发挥其冷却效果。因此必须考虑气膜对叶面的最适宜的覆盖效果。
前述那样将喷头冷却孔SC置于几何上对着气流方向,由于燃烧器旋流器的旋转方向的缘故,在叶尖侧TS与轮毂侧HS处,压力分布不同。
另外,为保证一定的薄膜冷却空气压力,只有仅有的一些部位(叶尖与轮毂中间部位)产生压差。因此,存在从冷却孔喷出的冷却空气流速下降,冷却效果受损的问题。
本发明即是为解决上述问题而作出的,不管是冷却孔的什么位置都保持一定的压力,而进行均匀的冷却。
本发明为解决前述问题,本发明提供的燃气轮机叶片的特征是,将在叶片前端部打的多个喷头冷却孔适应燃烧器旋流器的旋转方向,从叶尖一侧到轮毂一侧、从气流上游方向看靠近左右某一侧,且呈一线配置。这样,由于考虑了配置于上游的燃烧器的旋涡旋转方向,通过将喷头冷却孔于从叶尖到轮毂间配置于从气流上游看处在偏左侧或偏右侧的一条线上,使各冷却孔位置的压力沿叶长方向为一定,同时与冷却空气压力的压差也同样为一定,故可达到均匀冷却。
另外,本发明所提供的燃气轮机叶片上呈一线排列的多个喷头冷却孔,在燃烧器旋流器的旋转方向为右旋的情况下,从气流上游看,叶尖一侧的冷却孔比轮毂一侧的冷却孔更靠左侧,由于在配置于前述上游的燃烧器的旋涡旋转方向为右旋,从气流上游看,叶尖一侧冷却孔比轮毂一侧冷却孔更靠近左侧,在各冷却孔位置的压力沿叶长方向为一定,同时与冷却空气压力的压差也为一定,故可达到均匀冷却效果。
另外,本发明所提供的燃气轮机叶片上呈一线排列的多个喷头冷却孔,在燃烧器的旋涡旋转方向为左旋的情况下,从气流上游看,叶尖一侧的冷却孔比轮毂一侧的冷却孔更靠近右侧。在配置于前述上游的燃烧器的旋涡旋转方向为左旋时,通过将喷头冷却孔配置成从气流上游看,从叶尖一侧到轮毂一侧喷头冷却孔配置于靠右侧的线上,使在各冷却孔的位置压力沿叶长为一定,同时与冷却空气的压力差也为一定,能达到均匀冷却。
另外,本发明由于提供了从前述多个喷头冷却孔喷出冷却空气来冷却叶面的燃气轮机叶片,并采用冷却空气作为从喷头冷却孔喷出、冷却叶面的冷却媒体,从而达到了可靠的冷却效果。
图1是本发明的一实施例的燃气轮机叶片的喷头冷却孔斜视图;图2是将图1的喷头冷却孔的压力分布状态与现有冷却孔压力分布状态比较说明图;图3是表示现有燃气轮机叶片空冷结构剖视图;图4是表示现有燃气轮机叶片的喷头冷却孔的斜视图。
下面参照图1与图2说明本发明一实施形态。图1是燃气轮机空冷叶片斜视图;图2是将本实施形态的冷却孔穿孔位置与现有叶片对比的比较图。
图1中的1是喷头冷却孔,它是在叶片2的前端边缘从叶尖一侧TS到轮毂一侧HS呈一条线排列的多个通孔。而该喷头冷却孔1相应于图中箭头C所表示的燃烧器的旋涡旋转方向,其穿孔的位置错开着。
即,在如前述箭头C指示的方向,旋流器旋转方向为右旋的情况下,是将叶尖一侧TS的喷头冷却孔1的位置从叶片上游一侧看置于靠左侧(本实施形态中叶背一侧)A的位置;而随着到了轮毂一侧HS,喷头冷却孔1的位置,从叶片上游一侧看置于靠右侧(本实施形态中为叶片的腹侧)B的位置。而且,在燃烧器的旋涡旋转方向为左旋时,在与上述相反的位置打孔。
在本实施例中,如前所述,是使喷头冷却孔相应于旋涡的旋转方向而错开;将这种情况下空气流动与压力变化的状况同现有装置那样将冷却孔直线排列情况进行对比,即如图2所示。
即,如图2左侧X的位置所示那样,现有装置中从叶尖一侧TS到轮毂一侧HS直线打出冷却孔的情况下,相对于燃气流的压力分布P1的变化,冷却空气压力P2是一定的,而且位置固定,因此,其压差ΔP沿叶片2高度方向不同位置H1、H2、H3分别产生了不同的压差,流动状态也各不相同,得不到均一的冷却效果,特别是在叶片上H2部位,由于冷却空气流速降低,冷却效果大受损失。
与此相对,考虑旋涡的旋转方向,像本实例那样,所打出的喷头冷却孔1,由于相应于压力分布穿孔位置而错开,如图2中央部分y的位置所表示的那样,在沿高度方向H1、H2、H3各位置,对应于冷却空气压力P2可以得到一定的压力差ΔP,从而在任何位置上流动状态一定,冷却效果均一,冷却效率进一步提高。
以上,将本发明借图示实施例进行了说明,当然本发明也不限于该实施例,在本发明的范围内对其具体结构可做种种变更。
如上所述,如依照本发明,在高温燃气轮机叶片上,在从喷头冷却孔喷出冷却空气进行薄膜冷却时,由于从叶片叶尖到轮毂的冷却孔处的压力是一定的,这些位置的气流的流动状态都相同,故可进行均一的薄膜冷却。
因此,可以得到较高的薄膜冷却效率,叶片的可靠性进一步提高。
Claims (4)
1.一种燃气轮机叶片,其特征在于,将在叶片前部开设的多个喷头冷却孔,相应于燃烧器的旋涡旋转方向,从叶尖一侧到轮毂一侧、从上游侧看靠近左右某一侧配置于一条线上。
2.按权利要求1所记述的燃气轮机叶片,其特征在于,前述多个喷头冷却孔设置成,在燃烧器的旋涡旋转方向为右旋的情况下,从上游一侧看,叶尖一侧的冷却孔比轮毂一侧的冷却孔更靠左侧地配置于一条线上。
3.按权利要求1所记述的燃气轮机叶片,其特征在于,前述多个喷头冷却孔设置成,在燃烧器的旋涡旋转方向为左旋的情况下,从上游一侧看叶尖一侧的冷却孔比轮毂一侧的冷却孔更靠右侧地配置于一条线上。
4.按权利要求1、2或3所记述的燃气轮机叶片,其特征在于,从前述多个喷头冷却孔喷出冷却空气,来冷却叶片表面。
Applications Claiming Priority (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
JP302788/1995 | 1995-11-21 | ||
JP30278895A JP3477296B2 (ja) | 1995-11-21 | 1995-11-21 | ガスタービン翼 |
JP302788/95 | 1995-11-21 |
Publications (2)
Publication Number | Publication Date |
---|---|
CN1169175A true CN1169175A (zh) | 1997-12-31 |
CN1076782C CN1076782C (zh) | 2001-12-26 |
Family
ID=17913135
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
CN96191546A Expired - Fee Related CN1076782C (zh) | 1995-11-21 | 1996-11-20 | 燃气轮机叶片 |
Country Status (8)
Country | Link |
---|---|
US (1) | US5897294A (zh) |
EP (1) | EP0805263B1 (zh) |
JP (1) | JP3477296B2 (zh) |
KR (1) | KR100234467B1 (zh) |
CN (1) | CN1076782C (zh) |
CA (1) | CA2209851C (zh) |
DE (1) | DE69628818T2 (zh) |
WO (1) | WO1997019257A1 (zh) |
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN101878395B (zh) * | 2007-11-29 | 2012-08-29 | 三菱重工业株式会社 | 燃烧器 |
US8465255B2 (en) | 2008-05-14 | 2013-06-18 | Mitsubishi Heavy Industries, Ltd. | Gas turbine blade and gas turbine having the same |
CN104832218A (zh) * | 2015-04-20 | 2015-08-12 | 西北工业大学 | 一种用于涡轮叶片前缘气膜冷却的错位对冲气膜孔排结构 |
Families Citing this family (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP2807379B2 (ja) * | 1992-02-14 | 1998-10-08 | 株式会社日立製作所 | タンデム圧延機及び作業ロールクロスミル |
EP3094823B8 (en) | 2014-01-16 | 2021-05-19 | Raytheon Technologies Corporation | Gas turbine engine component and corresponding gas turbine engine |
CN113217462B (zh) * | 2021-06-08 | 2022-11-29 | 西北工业大学 | 亚声速旋涡吹气式压气机叶片 |
Family Cites Families (11)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3540811A (en) * | 1967-06-26 | 1970-11-17 | Gen Electric | Fluid-cooled turbine blade |
US3619082A (en) * | 1968-07-05 | 1971-11-09 | Gen Motors Corp | Turbine blade |
US3554663A (en) * | 1968-09-25 | 1971-01-12 | Gen Motors Corp | Cooled blade |
US3644060A (en) * | 1970-06-05 | 1972-02-22 | John K Bryan | Cooled airfoil |
GB1426049A (en) * | 1972-10-21 | 1976-02-25 | Rolls Royce | Rotor blade for a gas turbine engine |
JPS5177710A (ja) * | 1974-03-15 | 1976-07-06 | Nat Aerospace Lab | Gasutaabinyokoonbuzaino reikyakusochi |
GB2087980B (en) * | 1980-11-20 | 1984-03-14 | Rolls Royce | Liquid cooled aerofoil for a gas turbine engine and a method of making the aerofoil |
JPS6032903A (ja) * | 1983-08-01 | 1985-02-20 | Agency Of Ind Science & Technol | ガスタ−ビンの翼 |
US4808785A (en) * | 1986-11-13 | 1989-02-28 | Chromalloy Gas Turbine Corporation | Method and apparatus for making diffused cooling holes in an airfoil |
US5486093A (en) * | 1993-09-08 | 1996-01-23 | United Technologies Corporation | Leading edge cooling of turbine airfoils |
US5779437A (en) * | 1996-10-31 | 1998-07-14 | Pratt & Whitney Canada Inc. | Cooling passages for airfoil leading edge |
-
1995
- 1995-11-21 JP JP30278895A patent/JP3477296B2/ja not_active Expired - Fee Related
-
1996
- 1996-11-20 CN CN96191546A patent/CN1076782C/zh not_active Expired - Fee Related
- 1996-11-20 WO PCT/JP1996/003397 patent/WO1997019257A1/ja active IP Right Grant
- 1996-11-20 EP EP96938510A patent/EP0805263B1/en not_active Expired - Lifetime
- 1996-11-20 DE DE69628818T patent/DE69628818T2/de not_active Expired - Fee Related
- 1996-11-20 KR KR1019970704951A patent/KR100234467B1/ko not_active IP Right Cessation
- 1996-11-20 US US08/875,176 patent/US5897294A/en not_active Expired - Lifetime
- 1996-11-20 CA CA002209851A patent/CA2209851C/en not_active Expired - Fee Related
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN101878395B (zh) * | 2007-11-29 | 2012-08-29 | 三菱重工业株式会社 | 燃烧器 |
US8465255B2 (en) | 2008-05-14 | 2013-06-18 | Mitsubishi Heavy Industries, Ltd. | Gas turbine blade and gas turbine having the same |
CN104832218A (zh) * | 2015-04-20 | 2015-08-12 | 西北工业大学 | 一种用于涡轮叶片前缘气膜冷却的错位对冲气膜孔排结构 |
Also Published As
Publication number | Publication date |
---|---|
KR19980701560A (ko) | 1998-05-15 |
JP3477296B2 (ja) | 2003-12-10 |
DE69628818T2 (de) | 2004-05-19 |
EP0805263A4 (en) | 1999-10-20 |
JPH09144503A (ja) | 1997-06-03 |
CN1076782C (zh) | 2001-12-26 |
EP0805263B1 (en) | 2003-06-25 |
KR100234467B1 (ko) | 1999-12-15 |
EP0805263A1 (en) | 1997-11-05 |
CA2209851C (en) | 2000-05-02 |
DE69628818D1 (de) | 2003-07-31 |
US5897294A (en) | 1999-04-27 |
WO1997019257A1 (fr) | 1997-05-29 |
CA2209851A1 (en) | 1997-05-29 |
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