CN1721660A - 涡轮机翼片尾缘修理及其方法 - Google Patents
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Abstract
喷嘴组的翼片尾缘的尾缘块焊接到取下了损坏的尾缘部分的喷嘴组的翼片部分。该尾缘块包括薄膜冷却孔,孔沿该块的压力侧壁互相间隔开;和多个沿尾缘径向间隔开的开口。通过焊接该块的压力和吸入侧边到翼片的剩余部分的压力和吸入侧边,可延长喷嘴的使用寿命。
Description
技术领域
本发明涉及翼片尾缘的修理,具体地,涉及一种尾缘块,具有尾缘冷却结构,用于更换燃气轮机的喷嘴翼片的损坏尾缘部分。本发明还涉及修理翼片的尾缘部分的方法。
背景技术
燃气轮机的高操作效率已经通过更高燃烧温度和翼片,如喷嘴的不动翼片,的增强的空气动力学设计,得到实现。先进的涡轮机已经采用改进的冷却结构,尤其是翼片尾缘的冷却结构。应当认识到,涡轮机的气体流道中的热气体温度在第一级翼片,即喷嘴,接近1700到1800°F。对于更高的操作温度和翼片先进的空气动力学设计,已经采用改进的冷却结构来减少和减缓暴露于这些气体的翼片的损坏速率。已经提出和实施各种结构的尾缘冷却系统。例如,一种冷却系统包括多个穿过尾缘的径向间隔开的开口,并结合互相径向间隔开的薄膜冷却孔,各孔与相邻的尾缘轴向间隔开。薄膜冷却孔沿翼片的压力侧,即较热侧,设置,以便薄膜冷却其余的尾缘表面。带有这样先进的冷却结构的翼片已经设置到燃气轮机,并可延长涡轮机喷嘴的使用寿命,几乎是现有的冷却结构的使用寿命的2倍。结果是,燃气轮机可操作,即使用,相当长的时间才需要进行维修,相关的成本优势不仅表现在涡轮机效率,还表现在涡轮机的停机时间。
涡轮机翼片已经通过用新的替换尾缘部分更换损坏的尾缘部分进行修理。构成喷嘴翼片的替换尾缘部分的尾缘块焊接到翼片的其余的前和中间部分,翼片的损坏尾缘部分已经取下。迄今尾缘块尚不能用来大量延长涡轮机翼片的使用寿命,因为缺少所要求的冷却结构。目前使用的喷嘴在这些喷嘴的翼片严重损坏前只有有限的使用寿命,故限制了涡轮机的效率,并要求进行维修。例如,许多现有的涡轮机的翼片只有24,000小时的使用周期。尽管具有类似尾缘部分,如涡轮机现有的尾缘部分,的尾缘块可以或已经用于更换损坏的尾缘部分,修理过的喷嘴翼片的使用时间未极大地延长,预计只有与原来翼片类似的使用寿命。
喷嘴翼片一般设有多个喷嘴组,围绕涡轮机轴线以周边排列的方式设置。各个组包括内和外带圈或平台,其间延伸一个或多个喷嘴叶片,即翼片。各喷嘴组一般用贵金属铸造成。尽管可以用具有改进的冷却结构的新喷嘴组来整体更换喷嘴组,得到更长时间的使用期,但因为材料和实现更换所需的机械加工,这种代换的喷嘴组具有极高的成本。因此,需要一种尾缘块和修理涡轮机尾缘的方法,以延长修理喷嘴的使用寿命,并超过原来设置到涡轮机的喷嘴翼片的使用周期。
发明内容
根据本发明的优选方面,提供了一种尾缘块,其具有增强的冷却能力,可用于替换损坏的喷嘴翼片的尾缘部分,修理的翼片可提高涡轮机喷嘴的使用寿命。尾缘块包括多个薄膜冷却孔,一般沿块的压力侧在径向上互相间隔开;以及多个穿过尾缘的径向间隔开的开口。多个径向间隔开的肋部在块的相对的压力及吸入侧和块的前缘之间延伸,肋部有径向倒角以焊接到喷嘴翼片的剩余部分,损坏的尾缘部分已从翼片取下。通过焊接尾缘块到现有翼片剩余部分,修理翼片可具有延长的使用寿命。质量提高的翼片具有冷却结构,该结构对应于具有先进冷却结构的新翼片结构,使喷嘴组有延长的使用寿命。
本发明的优选实施例中,提出了一种物件,用于修理涡轮机喷嘴组,各喷嘴组具有内和外平台之间的翼片,取下翼片的尾缘部分,留下内和外平台之间的翼片的中间和前缘部分;物件包括尾缘块,具有压力和吸入侧壁部分;多个薄膜冷却孔,沿所述尾缘块的压力侧壁在径向上互相间隔开;所述尾缘块包括尾缘,其具有多个沿径向间隔开的开口;和多个沿径向间隔开的肋部,在所述块的相对的压力和吸入侧边之间延伸,压力和吸入侧壁部分的边带有倒角,用于焊接到所述翼片的中间部分的压力和吸入侧壁部分。
在本发明的另一优选实施例中,提出了一种修理的涡轮机喷嘴,包括:翼片前缘部分和翼片中间部分,及内平台和外平台,形成喷嘴组的剩余部分,喷嘴组取下了损坏的尾缘部分;尾缘块具有尾缘,压力侧和吸入侧壁部分,多个薄膜冷却孔,一般沿径向和所述块的压力侧壁部分互相间隔开;多个沿所述尾缘和径向间隔开的开口,和多个径向间隔开的肋部,在翼片的相对的压力和吸入侧之间延伸;焊缝位于剩余部分的相对的压力和吸入侧边,及所述尾缘块的各压力和吸入侧边,因此剩余部分和所述块在内和外平台之间形成完整的翼片。
在本发明的又一个优选实施例中,提出了一种修理涡轮机喷嘴组的翼片的方法,包括步骤:(a)取下所述翼片损坏的尾缘部分,留下包括前缘和中间部分的其余翼片部分;(b)提供尾缘块,其具有压力和吸入侧壁部分,多个薄膜冷却孔,一般沿径向和所述块的压力侧壁部分互相间隔开;和多个径向间隔开的开口,和多个径向间隔开的肋部,在所述翼片的相对的压力和吸入侧之间延伸;和(c)沿剩余翼片部分的相对的压力和吸入侧和所述块进行焊接,以固定所述块到其余的翼片部分。
附图说明
图1是形成涡轮机级的部分环形排列喷嘴的多个喷嘴组的部分轴向视图;
图2是安装到内和外壳体部分之间的喷嘴组的侧视图;
图3是穿过喷嘴组的翼片的放大的截面图,显示出焊接到原来喷嘴的可重新使用部分的尾缘块;
图4是用于修理喷嘴翼片的尾缘块的放大截面图;
图5是图4的尾缘块的放大侧视图;
图6是沿尾缘块的压力侧的薄膜冷却孔的放大图;和
图7到9是修理喷嘴翼片方式的示意图。
具体实施方式
现在参考图1,其显示了多个沿周边间隔设置的喷嘴组,用数字10表示,形成部分燃气轮机,并围绕涡轮机的轴线环形排列。应当认识到,各个喷嘴组10包括一个或多个喷嘴叶片或翼片12,其在内平台14和外平台16之间延伸。喷嘴翼片12以及平台14,16形成部分的穿过涡轮机沿轴向延伸的热气通道,并形成部分涡轮机级。图2和图3更具体地显示了喷嘴组10。在这个实施例中,一对翼片12形成部分喷嘴组10,分别在内和外平台14,16之间延伸。应当理解,各喷嘴组可包括一个或多个平台之间的翼片。图2还显示了保持环20和内支撑环22,喷嘴组固定到保持环,内支撑环具有槽24,可容纳径向向内延伸的内平台14的导轨26,以固定喷嘴组抵抗沿向后方向的轴向运动。
如前面所提到的,喷嘴翼片12在使用中经常开裂和氧化,必须进行更换。应当理解,对喷嘴组进行整体更换是不符合成本效益的,因为要考虑该部件的成本和涉及的劳动,以及进行更换所需的停机时间。此外,磨损的喷嘴翼片更换为新翼片一般在一定时间后将导致类似的开裂和氧化,必须在类似的一定使用周期内再次进行更换。因此,应当进行有效的维修,使其不仅可减少维修费用,还能够延长喷嘴翼片的寿命到比原来翼片更长的周期。
为了实现前面所讨论的,应当认识到有很多开裂和氧化的喷嘴翼片部分位于尾缘区。喷嘴翼片的位于尾缘区前面的区域不经受相同程度的开裂和氧化,因此与尾缘区相比具有延长的寿命。这样,可以取下喷嘴翼片的损坏的尾缘部分,用新的尾缘部分和尾缘块更换该部分,新的部分具有改进的性能,可延长修理的喷嘴翼片的寿命,极大地超过原来翼片的寿命,如超过原来翼片寿命的2倍。
参考图4到6,尾缘块30设置成具有压力和吸入侧壁部分32,34,分别终止于尾缘36。尾缘块30构成了取下的原来翼片的损坏尾缘部分的置换件。尾缘块30设置了冷却结构,可减缓修理的翼片的尾缘的氧化速率,因此尾缘块可使修理的翼片具有延长的使用寿命。尽管尾缘块30的冷却结构类似于正在使用的原来翼片的冷却结构,但这些冷却结构从未用于修理损坏喷嘴翼片的尾缘块。
现在具体参考图4到6,尾缘块30包括多个肋部38,其在尾缘区40内的径向间隔位置在压力和吸入侧32,34之间延伸。肋部38之间的径向间隔形成径向间隔的流道,可在修理的翼片内部沿轴向向后方向引导冷却空气,回到压力通风系统42。压力通风系统42基本沿径向在喷嘴翼片的内和外两端之间延伸。多个径向间隔开的通道44与压力通风系统42流体连通,沿轴向延伸并终止于尾缘块30的尾缘36的出口孔。因此,应当理解,在修理的翼片中流动的冷却空气一般沿轴向流动通过肋部38之间的通道,对流冷却翼片的侧面,并排出到压力通风系统42。冷却空气然后通过通道44和尾缘36排出,当空气从压力通风系统42流到尾缘36时冷却了翼片的相对侧面。
此外,沿尾缘块30的压力侧32设置了多个通常间隔开的薄膜冷却孔46。修理翼片内的冷却空气还流过薄膜冷却孔46,和沿修理翼片的压力侧壁32流动,薄膜冷却压力侧尾缘区。薄膜冷却孔46具有沿压力侧的外表面,其如图6中48所示端部是扩大的。端部沿径向和轴向后方向扩大,使得冷却空气薄膜分布到尾缘区40到尾缘区36的基本整个压力侧表面。通过薄膜冷却孔46,其扩大的表面以及延伸通过尾缘36的冷却通道44,容纳这些冷却结构的修理的翼片减少了氧化和开裂的可能性。
为了修理损坏的翼片,参考图7到9,喷嘴组从涡轮机取下。喷嘴组的翼片的损坏的尾缘区50从翼片12取下。具体地,分别沿压力和吸入侧和距尾缘一定距离切割翼片,并沿取下的尾缘区和内外平台14,16连接处进行切割。实施切割可通过水射流切割器,线切割机,或等离子焰炬,如图7中52示意性地显示。已经损坏的尾缘区50取下,如图8所示,留下沿原来翼片的压力和吸入侧的分离的边。对这些边进行清洗和加工,以容纳相应的尾缘块30的边54,56(见图4)。剩余的翼片部分分别包括中间部分53,55的前缘。
具体地,如图9所示,尾缘块30然后置于内和外平台之间,将压力和吸入侧边54,56焊接到翼片的剩余部分的压力和吸入侧边,形成具有与原来翼片相同的空气动力学特征结构的修理翼片。此外,应当认识到,修理翼片的尾缘的冷却结构已经通过取下损坏的尾缘区50改变,添加的尾缘块30带有上面介绍的冷却结构。
焊接尾缘块30到翼片的剩余部分可通过如TIG焊接方法来实现。焊缝57沿翼片的的相对侧面位于内和外平台之间,还位于尾缘块的径向外及内边和外及内平台之间。对焊缝进行清理以提供平滑的表面,需要时设置圆角59(见图9),并与在各个喷嘴组具有先进冷却结构的修理翼片结合。
这些部分然后设置到涡轮机。因为修理尾缘块具有新冷却结构,喷嘴翼片的使用寿命有极大的提高。开裂和氧化减少,进行修理的间隔时间极大地增加,如增加了2倍。
尽管已经通过最实际和优选的实施例对本发明进行了介绍,应当知道本发明不限于所公开的实施例,而是相反,应覆盖属于所附权利要求的精神和范围内的各种改进和等效设置。
零件表
10 | 喷嘴组 |
12 | 叶片或翼片 |
14 | 内平台 |
16 | 外平台 |
20 | 保持环 |
22 | 支撑环 |
24 | 槽 |
26 | 延伸轨 |
30 | 尾缘块 |
36 | 尾缘 |
38 | 肋部 |
40 | 尾缘区 |
42 | 压力通风系统 |
44 | 通道 |
46 | 冷却孔 |
48 | 扩口压力侧 |
50 | 尾缘区 |
52 | 焊矩 |
53 | 前缘 |
55 | 中间翼片 |
57 | 焊缝 |
59 | 圆角 |
32,34 | 侧壁部分 |
54,56 | 边 |
Claims (10)
1.一种用于修理涡轮机喷嘴组的物件,所述喷嘴组具有在内和外平台之间的翼片,翼片的尾缘部分取下,留下所述平台之间的翼片的中间和前缘部分,所述物件包括:
尾缘块(30),具有压力侧壁部分(32)和吸入侧壁部分(34);
多个薄膜冷却孔(46),沿所述尾缘块的压力侧壁在径向互相间隔开;
所述尾缘块包括尾缘(36),具有多个沿径向间隔开的开口(44);和
多个沿径向间隔开的肋部(36),在所述块的相对的压力和吸入侧边之间延伸,所述压力和吸入侧壁部分的边(54,56)带有倒角,用于焊接到所述翼片的中间部分的压力和吸入侧壁部分。
2.根据权利要求1所述的物件,其特征在于,所述孔(46)一般是圆柱形,通过所述块的压力侧壁部分的锥形部分使端部扩大(48),以从所述孔分配空气到压力侧壁部分的下游表面,使得薄膜冷却孔下游的所述块的基本整个尾缘部分。
3.根据权利要求1所述的物件,其特征在于,所述开口的数量超过所述薄膜冷却孔的数量至少两倍。
4.一种修理的涡轮机喷嘴,包括:
翼片前缘部分(53)和翼片中间部分(55),及内平台和外平台,形成了喷嘴组的剩余部分,所述喷嘴组取下了损坏的尾缘部分(50);
尾缘块,具有尾缘(36),压力侧和吸入侧壁部分(32,34),多个薄膜冷却孔(46),一般沿径向和沿所述块的压力侧壁部分互相间隔开;多个沿所述尾缘和径向间隔开的开口(44),和多个径向间隔开的肋部(38),在所述翼片的相对的压力和吸入侧之间延伸;
焊缝(55,57),位于所述剩余部分的相对的压力和吸入侧边,及所述尾缘块的各压力和吸入侧边,因此所述剩余部分和所述块在所述内和外平台之间形成完整的翼片。
5.根据权利要求4所述的修理过的喷嘴,其特征在于,所述开口的数量超过所述孔的数量至少两倍
6.根据权利要求4所述的修理过的喷嘴,其特征在于,所述孔(46)一般是圆柱形,通过所述块的压力侧壁部分的锥形部分使端部扩大(48),以从所述孔分配空气到压力侧壁部分的下游表面,使得薄膜冷却孔下游的所述块的基本整个尾缘部分。
7.一种修理涡轮机喷嘴组的翼片的方法,包括步骤:
(a)取下所述翼片的损坏的尾缘部分(50),留下包括前缘和中间部分(53,55)的其余翼片部分;
(b)提供尾缘块(30),其具有压力和吸入侧壁部分(32,34),和多个薄膜冷却孔(46),一般沿径向和沿所述块的压力侧壁部分互相间隔开;和多个径向间隔开的开口(49),和多个径向间隔开的肋部(38),在所述翼片的相对的压力和吸入侧之间延伸;和
(c)沿所述其余翼片部分的相对的压力和吸入侧和所述块焊接(55,57),以固定所述块到所述其余翼片部分。
8.根据权利要求7所述的方法,其特征在于,所述方法还包括焊接所述块相对的径向边到内和外平台(14,16)。
9.根据权利要求7所述的方法,其特征在于,所述方法还包括在所述块的相对的径向边和所述内外平台的连接处形成圆角(59)。
10.根据权利要求7所述的方法,其特征在于,所述步骤(b)包括提供尾缘块,其上的开口的数量超过所述孔的数量至少2倍。
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US10/829281 | 2004-04-22 | ||
US10/829,281 US20050235492A1 (en) | 2004-04-22 | 2004-04-22 | Turbine airfoil trailing edge repair and methods therefor |
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CN100422508C CN100422508C (zh) | 2008-10-01 |
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US (3) | US20050235492A1 (zh) |
JP (1) | JP2005307983A (zh) |
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2007
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CN102686356B (zh) * | 2009-12-23 | 2016-05-11 | 斯奈克玛 | 制造用于涡轮引擎叶片的金属加固件方法 |
CN102562178A (zh) * | 2010-12-21 | 2012-07-11 | 哈米尔顿森德斯特兰德公司 | 用于空气循环机的涡轮机喷嘴 |
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US20070172351A1 (en) | 2007-07-26 |
JP2005307983A (ja) | 2005-11-04 |
GB2413599B (en) | 2009-03-18 |
US20050235492A1 (en) | 2005-10-27 |
CN100422508C (zh) | 2008-10-01 |
FR2869250B1 (fr) | 2007-04-13 |
GB2413599A (en) | 2005-11-02 |
US20070184182A1 (en) | 2007-08-09 |
FR2869250A1 (fr) | 2005-10-28 |
US7484928B2 (en) | 2009-02-03 |
GB0507906D0 (en) | 2005-05-25 |
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