CN107002250A - 沿着冷却孔的排的长的连续的雕刻部 - Google Patents
沿着冷却孔的排的长的连续的雕刻部 Download PDFInfo
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Abstract
通过连续的长的雕刻部减少热障涂层的剥落行为并且延长TBC的寿命。
Description
本发明涉及陶瓷表面结构,其中,沿着冷却孔的排存在长的雕刻部。
高载荷的涡轮叶片和轮叶需要应用不同的保护技术,以便能够耐受高的热载荷。涡轮叶片和轮叶的前期需要陶瓷涂层和膜冷却技术以及内部冷却。
只要组合在操作期间起作用并且不发生剥落(spallation)或者未察觉出冷却孔堵塞,那么应用此种技术则是有用的。
膜冷却孔的制造可能是陶瓷涂层剥落的原因之一。
激光钻孔的一些特性(parameters)导致在陶瓷涂层内的裂纹,陶瓷涂层随后剥落并且限制了部件的操作。
另一方面,鉴于不能以低能量进行钻孔,因此不可能将激光钻孔的能量减小到非常低的水平。
因此,本发明的目的是提高陶瓷涂层的寿命并且防止TBC的整体剥落。
该问题通过根据权利要求1的陶瓷表面结构来解决。
在从属权利要求中,公开了可以彼此任意组合的进一步的改进,从而产生了另外的新的优点。
图1、图3、图4示出了TBC的表面以及冷却孔的排的顶部视图,
图2示出了图1的截面图。
通过实施聚合物掩蔽,能够引入在图1至图4中所建议的设计。聚合物掩蔽将提供沿着冷却孔的无陶瓷区域。
该制造过程具有如下优点:
·雕刻部不会像激光雕刻期间一样减小粘合涂层的厚度;
·可以在涂覆期间实施该步骤;
·在出现流延(casting)偏差和涂覆偏差的情况下,聚合物掩蔽将不会影响粘合涂层的厚度。
此种无陶瓷区域的宽度可以在1mm与2mm之间变化。
雕刻部的积极效果是剥落行为。在发生剥落的情况下,剥落的区域不会在宽的区域上延伸。
雕刻部的另一个积极效果是由于非APS区域而引入的涡流,这迫使热气体流如通过高尔夫球上的凹痕一样粘在壁部。在操作期间,将使陶瓷涂层内的台阶平滑,而且APS平滑过程将有助于使边缘中断。
以下积极效果与雕刻部有关:
·能够用现有设计进行改装;
·在剥落的情况下,将仅会影响受限制区域;
·较低的操作风险;
·减少激光钻孔之后的返修;
·适用于所有受剥落威胁的冷却孔排;
·适用于轮叶和叶片。
图1示出了陶瓷涂层25(图2)的顶部视图。
热障涂层25(TBC)是部件1的一部分,部件1具有基底22(图2),其中,在基底22的顶部上施用热障涂层25。该部件1具有至少一排7的冷却孔10'、10″......,在部件1的使用期间,所述至少一排7的冷却孔10'、10″......由根据箭头13,尤其是几乎垂直于排7的方向14的热气体溢满。方向14是直的,或者方向14只有一次或两次最大25°的斜率转折。
沿着冷却孔10'、10″......的排7的方向14,特别地仅在排7之前存在雕刻部16和/或在排7之后存在第二雕刻部19。
这些雕刻部16、19在TBC 25中是连续的、特别地是直的雕刻部。
雕刻部16、19,20、116,216、31(图3、图4)不是环状(endless)的,例如,不是圆形或者不是正方形或者不是封闭的环。
雕刻部16、19,20、116,216、31特别地起始于排7的起始处并且结束于排7的末端处。
在一排7之前和之后的彼此相邻的两个雕刻部16、19,20、116,216、31之间的距离特别地为1mm至2mm。
此外,雕刻部也可以仅布置在TBC 25中。
在图2中可以看到,雕刻部16、19具有直到基底22为止的深度。
然而,基底22的表面可以涂覆有金属粘合涂层,如NiCoCrAl加上可选的添加剂(Y、Re、Si、Ta......)。
图3、图4示出了弯曲形状的雕刻部20、116,216、31,其中,相对的弯曲雕刻部116、20;216、31的距离小于两个冷却孔10'、10″之间的距离,并且其不是直的(图4)而是多重弯曲的,或者是直的与多重弯曲的组合(图3)。
Claims (13)
1.一种部件(1),
所述部件(1)包括:
基底(22),
在所述基底(22)上的陶瓷热障涂层(25),
在所述基底(4)中以及在所述热障涂层(25)中沿一定方向(14)的至少一排(7)的冷却孔(10'、10”......),
其中所述热障涂层(25)具有至少一个雕刻部,
其特征在于,
所述至少一个雕刻部是沿着所述方向(14)的在所述至少一排(7)之前和/或之后的长的连续的雕刻部(16、19、116、20、216、31)。
2.根据权利要求1所述的部件,
其中所述雕刻部(16、19,20)是直的。
3.根据权利要求1或2中的一项或两项所述的部件,
其中所述雕刻部(116,216、31)是多重弯曲的。
4.根据前述权利要求中的一项或任意项所述的部件,
其中所述雕刻部(16、19,20、116,216、31)是长的且连续的,以及所述雕刻部(16、19,20、116,216、31)不是彼此连接的或者环状的。
5.根据前述权利要求中的一项或任意项所述的部件,
其中在所述热障涂层(25)中布置有数个雕刻部(16、19,20、116,216、31)。
6.根据权利要求中1、2、3、4或5中的一项或任意项所述的部件,
其中所述雕刻部(16、19,116、20,216、31)仅布置在一排(7)之前和之后。
7.根据权利要求中1、2、3、4、5或6中的一项或任意项所述的部件,
其中所述基底(22)具有金属覆盖涂层。
8.根据权利要求7所述的部件,
其中所述雕刻部(16、19,20、116,216、31)具有到达所述基底(4)上的金属涂层的外表面的深度。
9.根据前述权利要求中的一项或任意项所述的部件,
其中所述雕刻部(16、19,20、116,216、31)仅布置在所述热障涂层中,而未到达所述基底(4)或金属涂层。
10.根据前述权利要求中的一项或任意项所述的部件,
其中所述雕刻部(16、19,116,216、31)起始于排(7)的起始处而结束于排(7)的末端处。
11.根据前述权利要求中的一项或任意项所述的部件,
其中两个雕刻部(16、19,116,216、31)具有沿着溢流方向(13)的距彼此1mm至2mm的距离。
12.根据前述权利要求3至11中的一项或任意项所述的部件,
其中弯曲的雕刻部(116、20,216、31)到直的雕刻部(20)的距离或者弯曲的雕刻部(116、20,216、31)到弯曲的雕刻部(31)的距离小于这两个雕刻部的两个冷却孔(10'、10”)之间的距离。
13.根据前述权利要求中的一项或任意项所述的部件,
其中所述基底(22)是镍基超级合金或钴基超级合金。
Applications Claiming Priority (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP14195844.7A EP3029176A1 (en) | 2014-12-02 | 2014-12-02 | Long, continuous engraving along a row of cooling holes |
EP14195844.7 | 2014-12-02 | ||
PCT/EP2015/075390 WO2016087143A1 (en) | 2014-12-02 | 2015-11-02 | Long, continuous engraving along a row of cooling holes |
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CN107002250A true CN107002250A (zh) | 2017-08-01 |
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CN201580065045.XA Pending CN107002250A (zh) | 2014-12-02 | 2015-11-02 | 沿着冷却孔的排的长的连续的雕刻部 |
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US (1) | US20170314399A1 (zh) |
EP (2) | EP3029176A1 (zh) |
JP (1) | JP6445160B2 (zh) |
CN (1) | CN107002250A (zh) |
WO (1) | WO2016087143A1 (zh) |
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US11585224B2 (en) | 2020-08-07 | 2023-02-21 | General Electric Company | Gas turbine engines and methods associated therewith |
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US6074706A (en) * | 1998-12-15 | 2000-06-13 | General Electric Company | Adhesion of a ceramic layer deposited on an article by casting features in the article surface |
US20090017260A1 (en) * | 2001-08-02 | 2009-01-15 | Kulkarni Anand A | Segmented thermal barrier coating |
CN101772587A (zh) * | 2008-03-14 | 2010-07-07 | 西门子公司 | 冷却孔掩蔽方法和用于掩蔽冷却孔的掩蔽工艺的装置 |
US8317473B1 (en) * | 2009-09-23 | 2012-11-27 | Florida Turbine Technologies, Inc. | Turbine blade with leading edge edge cooling |
CN103069112A (zh) * | 2010-06-11 | 2013-04-24 | 西门子能量股份有限公司 | 涡轮发动机中的薄膜冷却部件壁 |
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US5073433B1 (en) * | 1989-10-20 | 1995-10-31 | Praxair Technology Inc | Thermal barrier coating for substrates and process for producing it |
US6461107B1 (en) * | 2001-03-27 | 2002-10-08 | General Electric Company | Turbine blade tip having thermal barrier coating-formed micro cooling channels |
US8852720B2 (en) * | 2009-07-17 | 2014-10-07 | Rolls-Royce Corporation | Substrate features for mitigating stress |
US9884343B2 (en) * | 2012-12-20 | 2018-02-06 | United Technologies Corporation | Closure of cooling holes with a filling agent |
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2014
- 2014-12-02 EP EP14195844.7A patent/EP3029176A1/en not_active Withdrawn
-
2015
- 2015-11-02 US US15/528,866 patent/US20170314399A1/en not_active Abandoned
- 2015-11-02 JP JP2017529371A patent/JP6445160B2/ja not_active Expired - Fee Related
- 2015-11-02 EP EP15790513.4A patent/EP3198057A1/en not_active Withdrawn
- 2015-11-02 WO PCT/EP2015/075390 patent/WO2016087143A1/en active Application Filing
- 2015-11-02 CN CN201580065045.XA patent/CN107002250A/zh active Pending
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US6074706A (en) * | 1998-12-15 | 2000-06-13 | General Electric Company | Adhesion of a ceramic layer deposited on an article by casting features in the article surface |
US20090017260A1 (en) * | 2001-08-02 | 2009-01-15 | Kulkarni Anand A | Segmented thermal barrier coating |
CN101772587A (zh) * | 2008-03-14 | 2010-07-07 | 西门子公司 | 冷却孔掩蔽方法和用于掩蔽冷却孔的掩蔽工艺的装置 |
US8317473B1 (en) * | 2009-09-23 | 2012-11-27 | Florida Turbine Technologies, Inc. | Turbine blade with leading edge edge cooling |
CN103069112A (zh) * | 2010-06-11 | 2013-04-24 | 西门子能量股份有限公司 | 涡轮发动机中的薄膜冷却部件壁 |
Also Published As
Publication number | Publication date |
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EP3198057A1 (en) | 2017-08-02 |
JP2018504544A (ja) | 2018-02-15 |
EP3029176A1 (en) | 2016-06-08 |
JP6445160B2 (ja) | 2018-12-26 |
US20170314399A1 (en) | 2017-11-02 |
WO2016087143A1 (en) | 2016-06-09 |
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