CN106917024B - 燃气涡轮机部件和用于制造这种燃气涡轮机部件的方法 - Google Patents

燃气涡轮机部件和用于制造这种燃气涡轮机部件的方法 Download PDF

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CN106917024B
CN106917024B CN201610993427.5A CN201610993427A CN106917024B CN 106917024 B CN106917024 B CN 106917024B CN 201610993427 A CN201610993427 A CN 201610993427A CN 106917024 B CN106917024 B CN 106917024B
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H-P.博斯曼恩
M.巴赖尼哈萨尼
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Abstract

本发明涉及燃气涡轮机部件和用于制造这种燃气涡轮机部件的方法。所述燃气涡轮机部件包括多个片状部分，其中片状部分中的至少一个由称为MAX相的三元陶瓷制成，其具有分子式Mn+ 1AXn，其中n=1、2、或3，M是前过渡金属诸如Ti、V、Cr、Zr、Nb、Mo、Hf、Sc、Ta，并且A是A族元素诸如Al、Si、P、S、Ga、Ge、As、Cd、In、Sn、Tl、Pb，并且X是C和/或N，其中M在40‑60at‑%范围内，A在10‑30at‑%范围内并且X在20‑40at‑%范围内，并且因此M+A+X在80‑100%范围内，以及0‑20%是上面未列出且由于杂质或氧化引入的其他元素，并且其中片状部分被接合。

Description

燃气涡轮机部件和用于制造这种燃气涡轮机部件的方法
技术领域
本发明涉及燃气涡轮机的技术。本发明涉及根据本发明的燃气涡轮机部件。
本发明进一步涉及用于制造这种燃气涡轮机部件的方法。
背景技术
如今，高效燃气涡轮机在非常高的热气体温度下操作。用于热燃气涡轮机部件的实际材料是密度为大约8 g/cm3的镍超合金。该相对高的密度在各种转子部件（例如叶片）上产生高的离心力。当燃气涡轮机变得更大时，该问题变得更严重。
另一方面，所谓的MAX相的三元陶瓷是已知的，其能够具有大约4 g/cm3的低密度。
该材料的详情例如公开在M. Radovic和M. W. Barsoum的下述文章中：MAXphases: Bridging the gap between metals and ceramics, American CeramicSociety Bulletin, Vol. 92, Nr. 3, p. 20-27（2013年4月）。
文献US 2010/0055492 A1公开了包括具有分子式Mn+1AXn的MAX相材料和金属成分的合成物，其中，M是前过渡金属，A是A族元素，X是C和N中的一者或两者，并且n=1-3，其中，MAX相材料限定多个孔；并且所述金属成分包括低熔点金属，其中，该金属占据所述孔中的至少一些。还公开了一种方法，其包括：提供多孔坯体，该坯体包括具有分子式Mn+1AXn的颗粒材料，其中，M是前过渡金属，A是A族元素，X是C和N中的一者或两者，并且n=1-3；以及用低熔点金属渗透坯体的至少一些孔，从而提供复合材料。
在过去，已经考虑在燃气涡轮机的技术领域中使用MAX相。
文献US 8,192,850 B2公开了包括燃烧涡轮机构件基底和在燃烧涡轮机构件基底上的粘结涂层的燃烧涡轮机构件。粘结涂层可包括Mn+1AXn（n=1、2、3），其中，M选自元素周期表的IIIB、IVB、VB、VIB和VII族及其混合物，其中，A选自元素周期表的IIIA、IVA、VA和VIA族及其混合物，并且其中，X包括碳和氮中的至少一者。热障涂层可在粘结涂层上。
文献WO 2014/149097 A2公开了包括具有翼型部分和尖端的涡轮发动机构件的涡轮发动机系统，该涡轮发动机构件具有结合到尖端的MAXMET复合材料。MAXMET复合材料具有在金属基体中的MAX相。
文献WO 2014/143266 A1描述了用于燃气涡轮发动机的抗振风扇导叶。风扇导叶包括由MAXMET复合材料制成的振动阻尼构件。阻尼构件可以是覆盖风扇导叶主体的一些或全部的盖子。替代性地，风扇导叶主体的部分或整个导叶主体可由MAXMET复合材料制成。该公开利用MAXMET复合材料在循环弹性变形期间展现的超高、完全可逆、非线性弹性滞后行为以便阻尼振动。
文献EP 2 905 271 A1涉及包括嵌入在陶瓷基体中的陶瓷纤维的陶瓷基复合材料CMC。纤维包括由MAX相制成的涂层。MAX相涂层能够直接涂布在纤维的表面上，或例如在额外涂覆层之间。改进了CMC的性质，优选的高温性能。
发明内容
本发明的目的是实现非常大的燃气涡轮机而不改变转子材料。
本发明的另一目的是提供用于燃气涡轮机的新材料的应用和用于制造具有降低的比密度和稳健机械强度的燃气涡轮机构件的新过程。
这些和其他目的通过根据本发明的燃气涡轮机部件和方法实现。
根据本发明的燃气涡轮机部件（其尤其暴露于燃气涡轮机内的高温和离心力）的特征在于，所述燃气涡轮机部件包括多个片状部分，其中，所述片状部分中的至少一个由被称为MAX相的三元陶瓷制成，所述MAX相具有分子式Mn+1AXn，其中n=1、2、或3，M是前过渡金属，诸如Ti、V、Cr、Zr、Nb、Mo、Hf、Sc、Ta，并且A是A族元素，诸如Al、Si、P、S、Ga、Ge、As、Cd、In、Sn、Tl、Pb，并且X是C和/或N，其中M在40-60 at-%（原子数百分比）的范围内，A在10-30 at-%的范围内并且X在20-40 at-%的范围内，并且因此M+A+X在80-100%的范围内，以及0-20%是上面没有列出且由于杂质或氧化引入的其他元素，并且其中，所述片状部分被接合。
根据本发明的实施例，所述片状部分通过螺栓连接、钎焊和互锁或这些的组合被接合以固定所述片状部分。
根据本发明的另一实施例，所述MAX相是单相Ti2AlC或两相Ti2AlC和Ti3AlC2的合成物，其中，Ti2AlC相的范围是60-95%。
根据本发明的又另一实施例，所述MAX相是单相Ti3SiC2或两相Ti3SiC2和Ti4SiC3的合成物，其中，Ti3SiC2相的范围是60-95%。
根据本发明的又另一实施例，所述MAX相是两个主相Ti3SiC2和Ti2AlC的混合物，其中，Ti3SiC2相的范围是40-90%，并且因此两个MAX相在50-100%的范围内，以及0-20%是其他MAX相或元素。
根据本发明的又一实施例，所述燃气涡轮机部件通过组合具有不同晶体取向的若干片状部分而具有各向异性材料性质。
在片状部分的一个中，晶体取向可在离心力的方向上，并且在片状部分的另一个中，晶体取向可垂直于离心力的方向。
根据本发明的另一实施例，所述燃气涡轮机部件通过组合具有呈不同取向的纤维的若干片状部分而具有各向异性材料性质。
根据本发明的另一实施例，所述燃气涡轮机部件是转子热屏蔽件。
本发明方法包括以下步骤：
a）提供被称为MAX相的三元陶瓷，其具有分子式Mn+1AXn，其中n=1、2、或3，M是前过渡金属，诸如Ti、V、Cr、Zr、Nb、Mo、Hf、Sc、Ta，并且A是A族元素，诸如Al、Si、P、S、Ga、Ge、As、Cd、In、Sn、Tl、Pb，并且X是C和/或N，因此M在40-60 at-%的范围内，A在10-30 at-%的范围内并且X在20-40 at-%的范围内，并且因此M+A+X在80-100%的范围内，以及0-20%是上面没有列出且由于杂质或氧化引入的其他元素；
b）制造多个片状部分，因此所述片状部分中的至少一个由所述MAX相制成；以及
c）接合所述片状部分以构造所述燃气涡轮机部件。
根据本发明方法的实施例，所述接合步骤c）包括螺栓连接、钎焊和互锁或这些的组合以固定所述片状部分。
根据本发明方法的另一实施例，组合具有不同晶体取向的片状部分以获得具有各向异性材料性质的燃气涡轮机部件。
根据本发明方法的又一实施例，使用纤维以获得具有各向异性材料性质的燃气涡轮机部件。
附图说明
现在借助于不同实施例并参考附图来更详细地解释本发明。
图1-3示出根据本发明的实施例将燃气涡轮机的示例性转子热屏蔽件设计
分割成待单独制造的三个单独片；
图4示出这些片在被单独地制造后如何被接合的第一示例；
图5示出这些片在被单独地制造后如何被接合的第二示例；
图6示出类似于图2的片，这些片具有不同的晶体取向以便获得各向异性
材料；以及
图7示出在热屏蔽件的顶部上具有单独部件（翅部）的转子热屏蔽件，该单独部件由MAX相制成并被插入到热屏蔽件的顶部上的凹部中。
具体实施方式
本发明关于使用新材料、设计和工艺过程来生产燃气涡轮机部件，尤其是燃气涡轮机的转子热屏蔽件，其中，新材料提供低密度并且因此降低转子上的离心力，并且新设计和工艺过程方法促进部件的制造。
这允许在不改变转子材料的情况下构造非常大的燃气涡轮机。这能够通过应用新材料和工艺过程以制造具有降低的比密度和稳健机械强度的部件来完成。
在这一点上，所谓的MAX相（三元陶瓷）是能够满足该要求的极其令人关注的选择，其密度为大约4-4.5 g/cm3、热膨胀系数＞8x10-6 K-1、700 ℃时的热导率>50 W/mK、断裂韧性>5 MPa.m1/2、以及高抗氧化性。
使用MAX相的所提出的解决方案将解决氧化问题，尤其是在转子热屏蔽件13的翅部14’上的氧化问题，如在图7中所示。
MAX相（其用于通过粉末冶金过程来生产热涡轮机部件）是具有Mn+1AXn分子式的陶瓷族，其中，n=1、2、或3，M是前过渡金属，诸如Ti、V、Cr、Zr、Nb、Mo、Hf、Sc、Ta，并且A是A族元素，诸如Al、Si、P、S、Ga、Ge、As、Cd、In、Sn、Tl、Pb，并且X是C和/或N。M在40-60 at-%的范围内，A在10-30 at-%的范围内并且X在20-40 at-%的范围内。并且M+A+X在80-100%的范围内以及0-20 %的元素，所述元素在上面没有列出且是由于杂质或氧化引入的。
MAX相的一个优选合成物是单相Ti2AlC，或两相Ti2AlC和Ti3AlC2（211和312），其中，211相的范围是60-95%。
MAX相的另一优选合成物是单相Ti3SiC2，或两相Ti3SiC2和Ti4SiC3（312和413），其中，312相的范围是60-95%。
MAX相的另一优选合成物是两个主相Ti3SiC2和Ti2AlC的混合物，其中，Ti3SiC2相的范围是40-90%，并且因此两个MAX相在50-100%的范围内，以及0-20%为其他MAX相或元素。
尤其，燃气涡轮机的转子热屏蔽件（该部件）通过粉末技术过程由MAX相生产。转子热屏蔽件例如在文献EP 1 079 070 A2的图2中示出。
本申请的图1示出转子热屏蔽件10的设计，其安装在燃气涡轮机的转子上以保护转子免受热气体路径的热气体温度的影响。T形转子热屏蔽件10具有底部部分11，其与转子的未示出的根部区段接触。在其上侧上具有多个平行翅部14的顶部部分13与在涡轮机的定子部件（未示出）处的静止轮叶的尖端接触。顶部部分13和底部部分11通过中间部分12连接。当转子热屏蔽件10与转子一起旋转时，其受到离心力CF，该离心力的方向在图1和图3中由箭头标记。
转子热屏蔽件10（在图1-3中示出的示例中）沿着离心力F的方向被分割成三个独立的片状部分10a、10b和10c。其他分割也是可能的。三个片状部分10a、10b和10c中的一个、两个或所有部分由具有Mn+1AXn分子式的MAX相制成，其中，n=1、2、或3，M是前过渡金属，诸如Ti、V、Cr、Zr、Nb、Mo、Hf、Sc、Ta，并且A是A族元素，诸如Al、Si、P、S、Ga、Ge、As、Cd、In、Sn、Tl、Pb，并且X是C和/或N。M在40-60 at-%的范围内，A在10-30 at-%的范围内并且X在20-40at-%的范围内。并且M+A+X在80-100%的范围内以及0-20%的元素，所述元素在上面没有列出且是由于杂质或氧化引入的。
根据图4和图5，然后通过螺栓连接、钎焊和利用螺栓15和相应互锁件16（图4）或17（图5）的互锁来接合片状部分10a、10b和10c，或使用这些的组合来固定所述部分。
因为当前转子热屏蔽件通常由于热机械负载和不同质量分布的加热和冷却而弯曲，因此进一步提出，提供具有由若干片状部分10a、10b和10c（参见图6）产生的各向异性材料的转子热屏蔽件，其中，在一个片状部分中，晶体取向在离心力的方向上，并且在另一片状部分中，晶体结构垂直于离心力的方向。在图6中，该不同的晶体取向由不同阴影线示出。
这对于T形转子热屏蔽件（包括与轮叶尖端/护罩接触的顶部部分13和与根部区段接触的底部部分11）尤其有益，其中，顶部部分13由于不同取向和MAX相的高热导率的组合而不弯曲。
作为不同晶体取向的替代方式，各向异性材料性质可利用不同取向的浸渍纤维来产生。
此外，根据另一实施例，如在图7中示出的，在热屏蔽件的顶部上的单独部件（翅部14’）可由MAX相制成，该翅部14’可被插入到在热屏蔽件13的顶部上的相应凹部中。
参考数字列表
10 转子热屏蔽件（T形）
10a-c 片状部分
11 底部部分（与根部区段接触）
12 中间部分
13 顶部部分（与轮叶尖端接触）
14、14’ 翅部
15 螺栓
16、17 互锁件
CF 离心力。

Claims (13)

1.一种燃气涡轮机部件（10），其暴露于燃气涡轮机内的高温和离心力，其特征在于，所述燃气涡轮机部件（10）包括多个片状部分（10a、10b、10c），其中，所述片状部分（10a、10b、10c）中的至少一个由被称为MAX相的三元陶瓷制成，所述MAX相具有分子式Mn+1AXn，其中，n=1、2、或3，M是前过渡金属，诸如Ti、V、Cr、Zr、Nb、Mo、Hf、Sc、Ta，并且A是A族元素，诸如Al、Si、P、S、Ga、Ge、As、Cd、In、Sn、Tl、Pb，并且X是C和/或N，因此M在40-60 at-%的范围内，A在10-30at-%的范围内并且X在20-40 at-%的范围内，并且因此M+A+X在80-100 at-%的范围内，以及0-20 at-%是上面没有列出且由于杂质或氧化引入的其他元素，并且其中，所述片状部分（10a、10b、10c）被接合。
2.如权利要求1所述的燃气涡轮机部件，其特征在于，所述片状部分（10a、10b、10c）通过螺栓连接、钎焊和互锁或这些方法的组合被接合以固定所述片状部分（10a、10b、10c）。
3.如权利要求1所述的燃气涡轮机部件，其特征在于，所述MAX相是单相Ti2AlC或两相Ti2AlC和Ti3AlC2的合成物，其中，所述Ti2AlC相的范围是60-95 %。
4.如权利要求1所述的燃气涡轮机部件，其特征在于，所述MAX相是单相Ti3SiC2或两相Ti3SiC2和Ti4SiC3的合成物，其中，所述Ti3SiC2相的范围是60-95 %。
5.如权利要求1所述的燃气涡轮机部件，其特征在于，所述MAX相是两个主相Ti3SiC2和Ti2AlC的混合物，其中，所述Ti3SiC2相的范围是40-90 %，并且因此两个主相在50-100 %的范围内，以及0-20 %是其他MAX相或元素。
6.如权利要求1所述的燃气涡轮机部件，其特征在于，所述燃气涡轮机部件（10）通过组合具有不同晶体取向的若干片状部分（10a、10b、10c）而具有各向异性材料性质。
7.如权利要求6所述的燃气涡轮机部件，其特征在于，在所述片状部分（10a、10b、10c）的一个中，晶体取向在离心力（CF）的方向上，并且在所述片状部分（10a、10b、10c）的另一个中，晶体取向垂直于所述离心力（CF）的方向。
8.如权利要求1所述的燃气涡轮机部件，其特征在于，所述燃气涡轮机部件（10）通过组合具有呈不同取向的纤维的若干片状部分（10a、10b、10c）而具有各向异性材料性质。
9.如权利要求1所述的燃气涡轮机部件，其特征在于，所述燃气涡轮机部件（10）是转子热屏蔽件。
10.一种用于制造如权利要求1所述的燃气涡轮机部件（10）的方法，其包括如下步骤：
a）提供被称为MAX相的三元陶瓷，所述MAX相具有分子式Mn+1AXn，其中，n=1、2、或3，M是前过渡金属，诸如Ti、V、Cr、Zr、Nb、Mo、Hf、Sc、Ta，并且A是A族元素，诸如Al、Si、P、S、Ga、Ge、As、Cd、In、Sn、Tl、Pb，并且X是C和/或N，因此M在40-60 at-%的范围内，A在10-30 at-%的范围内并且X在20-40 at-%的范围内，并且因此M+A+X在80-100 at-%的范围内，以及0-20 at-%是上面没有列出且由于杂质或氧化引入的其他元素；
b）制造多个片状部分（10a、10b、10c），其中所述片状部分（10a、10b、10c）中的至少一个由所述MAX相制成；以及
c）接合所述片状部分（10a、10b、10c）以构造所述燃气涡轮机部件（10）。
11.如权利要求10所述的方法，其特征在于，所述接合步骤c）包括螺栓连接、钎焊和互锁或这些的组合以固定所述片状部分（10a、10b、10c）。
12.如权利要求10所述的方法，其特征在于，具有不同晶体取向的片状部分（10a、10b、10c）被组合以获得具有各向异性材料性质的燃气涡轮机部件（10）。
13.如权利要求10所述的方法，其特征在于，使用纤维以获得具有各向异性材料性质的燃气涡轮机部件（10）。
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US10570742B2 (en) 2020-02-25
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EP3168205A1 (en) 2017-05-17
US20170138199A1 (en) 2017-05-18

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