CN108602325A - 局部双层热障涂层 - Google Patents

局部双层热障涂层 Download PDF

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CN108602325A
CN108602325A CN201680069262.0A CN201680069262A CN108602325A CN 108602325 A CN108602325 A CN 108602325A CN 201680069262 A CN201680069262 A CN 201680069262A CN 108602325 A CN108602325 A CN 108602325A
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local strengthening
strengthening portion
ceramic layer
barrier coating
thermal barrier
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CN108602325B (zh
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F·阿马德
D·科赫
R·拉杜罗维克
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Siemens Energy Global GmbH and Co KG
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    • C23C28/00—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D
    • C23C28/30—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer
    • C23C28/34—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates
    • C23C28/345—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates with at least one oxide layer
    • C23C28/3455—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates with at least one oxide layer with a refractory ceramic layer, e.g. refractory metal oxide, ZrO2, rare earth oxides or a thermal barrier system comprising at least one refractory oxide layer
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    • C04B2237/00—Aspects relating to ceramic laminates or to joining of ceramic articles with other articles by heating
    • C04B2237/30—Composition of layers of ceramic laminates or of ceramic or metallic articles to be joined by heating, e.g. Si substrates
    • C04B2237/32—Ceramic
    • C04B2237/34—Oxidic
    • C04B2237/345—Refractory metal oxides
    • C04B2237/348—Zirconia, hafnia, zirconates or hafnates
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    • C04B2237/00—Aspects relating to ceramic laminates or to joining of ceramic articles with other articles by heating
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Abstract

通过用第二材料形成热障涂层的局部较厚部分，热障涂层系统可以更耐用或在更高温度下使用。

Description

局部双层热障涂层
技术领域
本发明涉及一种热障涂层系统，该热障涂层系统具有热障涂层、局部施加于高应力区的双层热障涂层。
背景技术
陶瓷热障涂层(TBC)用于保护在高温下使用的部件免受热输入。涡轮叶片就是这种情况。例如，EP2845924A1公开了使用包括第一陶瓷层的涂层系统，第一陶瓷层为完全稳定或者部分稳定的氧化锆，并且在第一陶瓷层上具有诸如锆酸钆的烧绿石结构的层。
由于涡轮中涡轮叶片的热应力较高，涡轮叶片的压力区会出现局部温度峰值。这会导致消耗更多的金属保护层或者导致TBC剥落。
使用冷却气孔会导致消耗压缩空气，进而降低效率。
在不采取任何措施的情况下，涡轮的最大运行时间将会缩短。
发明内容
因此，本发明的目标在于解决上述问题。
该目标通过根据权利要求1所述的涂层系统来实现。
附图说明
在附图中：
图1示出具有涂层系统的部件，并且
图2至图5示出根据本发明的构造的各种视图。
附图和说明仅示出本发明的示例性实施例。
具体实施方式
图1示出穿过涡轮叶片1的叶片翼型的横截面。
涡轮叶片1具有吸力侧7和压力侧4，涡轮叶片1在流入边缘10处受到热气流，并且涡轮叶片1包括流出边缘13。
在涡轮叶片1的情况下，在压力侧4的区域内存在高应力区22。
热气体围绕涡轮叶片1沿流动方向11流动。
图2示出涡轮叶片1的平面图，其中简化示出叶片翼型19和紧固区16。
在局部区域22，存在增加的热应力。在该区域内，具有局部加强部36、36'、36"(图3、图4和图5)。
局部加强部36、36'、36"优选地被布置为靠近平台21，并且优选可以与过渡区39(图5)一起在整个压力侧4沿流动方向11延伸。
在与流动方向11垂直的方向或径向方向上，即方向40上，局部加强部36、36'、36"的伸展最大为50％，尤其是最大30％。在涡轮叶片1的情况下，上述说明优选仅涉及叶片翼型19。
为了满足这种增加的热应力，热障涂层的厚度被局部增加。
图3和图4示出根据本发明的构造的横截面图。
层厚度的增加不是通过施加更多与周围层33的材料相同的材料，而是通过局部施加与第一材料不同的第二材料来实现。
第一陶瓷层33被布置在涡轮叶片1的叶片翼型19和叶片平台21上。
优选地，涡轮叶片1上的热障涂层33为锆基层，尤其是部分稳定的氧化锆层，并且加强的TBC是通过局部施加烧绿石层36、36'、36"，尤其是局部施加基于锆酸钆的烧绿石层来实现的。
局部加强部36、36'、36"的材料同样优选为完全稳定的氧化锆。
局部加强部36、36'、36"的材料的孔隙率优选地被设计为比第一陶瓷层33的孔隙率高至少10％、尤其是20％。
特别地，与第一陶瓷层33类似，局部加强部36、36'、36"也包括部分稳定的氧化锆。
在这种情况下，如图3所示，局部加强部36、36'、36"的第二材料可以施加至下方的陶瓷层33，换言之，加强部36'下方的热障涂层33的层厚度与包围局部加强部36'的热障涂层33的层厚度相同。
类似地，在局部加强部36"的区域内，也可以使下方的热障涂层33略薄，从而形成凹部34，其他材料被局部施加在凹部34中，准确地说是以获得增加厚度的方式施加(图4)在凹部34中。
第一陶瓷层33的厚度优选在350μm～500μm之间。
局部加强部36、36'、36"的厚度优选厚达300μm，尤其是厚达250μm。
优选地，局部加强部36、36'、36"比第一陶瓷层33薄至少10％，尤其是至少30％。
图5仅示出部件1的叶片翼型区19的平面图。
在仅具有第一热障涂层33的区与仅包含局部加强部36、36'、36"的区之间(图3和4)，可以存在过渡区39，该过渡区39具有第一陶瓷层33和局部加强部36'、36"的成分的梯度。
过渡区39也代表局部区域。

Claims (12)

1.一种陶瓷热障涂层系统，
至少包括：
一个基底(30)，
所述基底(30)上的可选的一层金属键合层，
其中在所述基底(30)上或可选地在所述金属键合层上，存在作为热障涂层的第一陶瓷层(33)，
所述第一陶瓷层(33)保护大部分或者完全暴露于高温区域的所述基底(30)，并且
所述热障涂层存在局部增强部(36、36'、36")用于局部加强热障，
其中所述增强部(36、36'、36")包括与所述第一陶瓷层(33)的材料不同的材料，
其中所述局部加强部(36、36'、36")包括所述热障涂层的面积的最多50％。
2.根据权利要求1所述的涂层系统，
其中所述第一陶瓷层(33)的材料包括氧化锆，尤其是部分稳定的氧化锆。
3.根据权利要求1-2中的一项或两项所述的涂层系统，
其中所述局部加强部(36、36'、36")的材料包括烧绿石，尤其是包括锆酸钆的烧绿石。
4.根据权利要求1-2中的一项或两项所述的涂层系统，
其中所述局部加强部(36、36'、36")的材料包括完全稳定的氧化锆。
5.根据权利要求1-4中的一项或多项所述的涂层系统，
其中所述局部加强部(36、36'、36")的材料的孔隙率比所述第一陶瓷层(33)的材料的孔隙率高至少10％、尤其是20％，
类似地，所述局部加强部(36、36'、36")的材料尤其地包括部分稳定的氧化锆。
6.根据前述权利要求中的一项或多项所述的涂层系统，
其中所述局部加强部(36、36")存在于所述第一陶瓷层(33)的凹部(34)中。
7.根据权利要求1-5中的一项或多项所述的涂层系统，
其中在所述第一陶瓷层(33)不减少层厚度的情况下，所述局部加强部(36')被布置在所述第一陶瓷层(33)上方。
8.根据前述权利要求中的一项或多项所述的涂层系统，
其中在所述局部加强部(36、36'、36")与周围的所述第一陶瓷层(33)之间存在一个成分过渡区(39)。
9.根据前述权利要求中的一项或多项所述的涂层系统，
其中所述第一陶瓷层(33)被布置在涡轮叶片(1)的叶片翼型(19)和叶片平台(21)上。
10.根据前述权利要求中的一项或多项所述的涂层系统，
其中所述局部加强部(36、36'、36")包括所述热障涂层面积的最多30％，尤其是在所述涡轮叶片的情况下，所述局部加强部在所述叶片翼型上包括所述热障涂层的面积的最多50％，尤其是最多30％。
11.根据前述权利要求中的一项或多项所述的涂层系统，
其中在所述局部加强部(36、36'、36")的区域中，所述局部加强部(36、36'、36")被设计为比下方的所述第一陶瓷层(33)薄至少10％，尤其是至少30％。
12.根据前述权利要求中的一项或多项所述的涂层系统，
其中所述第一陶瓷层(33)的厚度在350μm～500μm之间，和/或
所述局部加强部(36、36'、36")的厚度厚达300μm，尤其是厚达250μm。
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US10662787B2 (en) 2020-05-26
EP3347200B1 (de) 2019-08-21
CN108602325B (zh) 2020-03-17
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WO2017089082A1 (de) 2017-06-01
EP3347200A1 (de) 2018-07-18

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