CN115135852A - 具有含铪的镍基基材的经涂覆涡轮机部件 - Google Patents

具有含铪的镍基基材的经涂覆涡轮机部件 Download PDF

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CN115135852A
CN115135852A CN202180013454.0A CN202180013454A CN115135852A CN 115135852 A CN115135852 A CN 115135852A CN 202180013454 A CN202180013454 A CN 202180013454A CN 115135852 A CN115135852 A CN 115135852A
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J·德劳特瑞
S·哈玛迪
A·帕斯奎特
V·杰凯特
F·佩德拉扎迪亚兹
C·P·奥迪克
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Safran Aircraft Engines SAS
Centre National de la Recherche Scientifique CNRS
La Rochelle Universite
Safran SA
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La Rochelle Universite
Safran SA
SNECMA SAS
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    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
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Abstract

本发明涉及一种涡轮机部件(20)，所述部件(20)包含：(i)镍基超合金基材(21)，以质量含量计，其包含5.0％至8.0％钴、6.5％至10％铬、0.5％至2.5％钼、5.0％至9.0％钨、6.0％至9.0％钽、4.5％至5.8％铝、质量含量大于或等于2000ppm的铪，并任选地包含质量含量小于或等于1.5％的铌，以及任选地各自质量含量小于或等于100ppm的碳、锆和硼中的至少一种，其余部分由镍和不可避免的杂质组成；以及(ii)覆盖基材的β‑结构化镍铝化物涂层(22)。

Description

具有含铪的镍基基材的经涂覆涡轮机部件
技术领域
本发明涉及镍基超合金领域，更精确地说涉及用于航空领域的超合金。
背景技术
众所周知，一方面镍基超合金即使在高温下也具有较高的机械强度，另一方面镍基超合金具有良好的抗氧化性。由于这两个特性，其是航空领域涡轮机部件的首选材料。
在已知的镍基超合金中，可以特别提及商品名为AM-1的合金，该合金对应于文件US 4639280中描述的组合物。
超合金的抗氧化性可以通过在超合金表面形成涂层来进一步提高。然而，即使有这样的涂层，当前可获得的AM-1基合金在用于涡轮机时最终也会氧化。因此，仍然需要进一步提高涡轮机部件用超合金的抗氧化性。
发明内容
为此，发明人提供了一种涡轮机部件，所述部件包含：
(i)镍基超合金基材，以质量含量计，其包含5.0％至8.0％钴、6.5％至10％铬、0.5％至2.5％钼、5.0％至9.0％钨、6.0％至9.0％钽、4.5％至5.8％铝、质量含量大于或等于2000ppm的铪，并任选地包含质量含量小于或等于1.5％的铌，以及任选地各自质量含量小于或等于100ppm的碳、锆和硼中的至少一种，其余部分由镍和不可避免的杂质组成；以及
(ii)覆盖基材的β-结构化镍铝化物涂层。
优选地，铪质量含量小于或等于15000ppm。
本发明提供了一种通过基材形成并且涂覆有β-结构化镍铝化物的涡轮机部件，所述基材的组成与AM-1类似但经改性以具有相对高的铪含量(至少2000ppm)。发明人已经观察到，由涂覆有该特定涂层的这种基材形成的该部件具有特别高的抗氧化性。不希望受理论限制，发明人认为通过确保铪可以迁移到表面并形成保护性氧化物，而不是作为碳化物被困在材料中，基材中有限的碳含量有助于提高部件的抗氧化性。
优选地，基材中的铪质量含量可以大于或等于4000ppm。
在优选的实施方式中，基材中的铪质量含量可以大于或等于6000ppm。
发明人已经发现铪含量越高，抗氧化性越好。
在一个实施方式中，超合金是单晶。单晶超合金允许铪以更大量更快地向表面迁移，因为铪不会被通常引入以使多晶合金晶界稳定的碳所捕获。这进一步改善了铪赋予的保护，从而提高了部件的抗氧化性。
在一个实施方式中，β结构化镍铝化物涂层可以是β结构化NiAl。应注意的是，通常β结构化镍铝化物涂层可以被或不被一种或多种元素改性，所述一种或多种元素为例如铂、锆或铪。因此，作为适用于本发明的β结构化镍铝化物涂层，可以具体由β结构化NiAl、β结构化NiPtAl、β结构化NiAlZr和β结构化NiAlHf制成。
在一个实施方式中，β结构化镍铝化物涂层是β结构化NiAl涂层或β结构化NiPtAl涂层。
β结构化镍铝化物涂层可以通过本领域已知的方法形成。例如，β结构化镍铝化物涂层的形成可以具体通过物理气相沉积、化学气相沉积、固体渗碳或经由浆料工艺进行。
在一个实施方式中，根据本发明的涡轮部件还可以包括存在于β结构化镍铝化物涂层上的热屏障。
该热屏障本身是已知的，并且可以保护涡轮机部件抵御其使用期间遇到的高温。
在一个实施方式中，热屏障可以与β结构化镍铝化物涂层接触的方式存在。
在一个实施方式中，涡轮机部件可以是涡轮机分配器(turbomachinedistributor)或涡轮机分配器扇区(turbomachine distributor sector)。分配器可以是高压分配器或低压分配器。
在替代性实施方式中，涡轮机部件也可以是移动叶片(moving vane)或涡轮环扇区(turbine ring sector)。
根据其另一方面，本发明还涉及包含如上所述的部件的涡轮机。
附图说明
[图1]图1示意性且部分显示了根据本发明一个实施方式的涡轮机分配器的一部分。
[图2]图2示意性且部分显示了根据本发明一个实施方式的涡轮机部件的截面图。
[图3]图3是显示根据本发明的部件和本发明之外的部件之间抗氧化性差异的对比测试结果。
具体实施方式
现在将借助于附图进行描述，其旨在更好地理解本发明，而不应以限制性的方式进行解释。
通常，涡轮机涡轮包括固定元件和可移动元件。可移动元件可以是承载叶片的可移动轮，并且通常插入固定叶片组之间，也称为分配器。分配器/可移动轮对形成了涡轮级。
图1显示了涡轮机分配器10的一部分。
涡轮机分配器10可以包括外部平台2和内部平台4，固定叶片6在外部平台2与内部平台4之间延伸，意图以有利于相邻可移动轮(未显示)驱动的方向引导气流。
图2示意性显示了包含基材21和覆盖下层基材21的β结构化镍铝化物涂层22的涡轮机部件20。
此外，在所示实施方式中，涡轮机部件20还包括与β结构化镍铝化物涂层22接触的热屏障23。热屏障23可以限定部件20的外表面。
在一个实施方式中，涂层22的厚度e1可以为40μm至90μm。
同样，热屏障23的厚度e2可以为50μm至300μm。
在一个实施方式中，热屏障可以选自用氧化钇或一种或多种其他稀土氧化物部分稳定的氧化锆、掺杂有镝的氧化锆、锆酸钆、钙钛矿。
在替代的实施方式中，可以不存在热屏障23。在该情况下，β结构化镍铝化物涂层22可以限定部件的外表面。
实施例
多个AM-1样品富集有340ppm至8000ppm的铪质量含量。因此，当铪水平大于或等于2000ppm时生产了根据本发明的样品，并且生产了在本发明之外的其他样品。
样品仅改变其铪质量含量。
由此制备的样品的铪含量通过质谱进行测定。样品涂覆有铂改性的β结构化镍铝化物NiPtAl涂层。随后，各样品经受氧化循环，并且在前200次循环中每周测量各样品质量变化三次，然后每周测量两次。
氧化循环对应于非常快速地加热至氧化温度(1150℃±5℃)，在大气压力下在1150℃保持60分钟，最后用干燥空气强制冷却15分钟，以确保室温低于150℃±3℃。在6000次氧化循环后或观察到20mg/cm2的比质量变化时，停止测试。
图3显示了各样品获得的结果。图3中所示样品的铪质量含量为：曲线11为340ppm，曲线12为780ppm，曲线13为670ppm，曲线14为1300ppm，曲线15为2100ppm，曲线16为4700ppm，并且曲线17为8000ppm。
由图3可见，铪含量大于2000ppm(15、16、17)的样品也是质量损失最低的样品。因此，高铪含量允许获得较好的抗氧化性。
术语“……至……”应理解为包括端值。

Claims (8)

1.一种涡轮机部件(20)，其包含：
(i)镍基超合金基材(21)，以质量含量计，其包含5.0％至8.0％钴、6.5％至10％铬、0.5％至2.5％钼、5.0％至9.0％钨、6.0％至9.0％钽、4.5％至5.8％铝、质量含量大于或等于2000ppm的铪，并任选地包含质量含量小于或等于1.5％的铌，以及任选地各自质量含量小于或等于100ppm的碳、锆和硼中的至少一种，其余部分由镍和不可避免的杂质组成；以及
(ii)覆盖基材的β-结构化镍铝化物涂层(22)。
2.如权利要求1所述的涡轮机部件(20)，其中，基材(21)中铪质量含量大于或等于4000ppm。
3.如权利要求2所述的涡轮机部件(20)，其中，基材(21)中铪质量含量大于或等于6000ppm。
4.如权利要求1至3中任一项所述的涡轮机部件(20)，所述涡轮机部件还包含存在于β结构化镍铝化物涂层上的热屏障(23)。
5.如权利要求1至4中任一项所述的涡轮机部件(20)，其中，β结构化镍铝化物涂层(22)是β结构化NiAl涂层或β结构化NiPtAl涂层。
6.如权利要求1至5中任一项所述的涡轮机部件(20)，其中，超合金是单晶。
7.如权利要求1至6中任一项所述的涡轮机部件(20)，其中，所述部件是涡轮机分配器(10)或涡轮机分配器扇区。
8.一种涡轮机，其包括如权利要求1至7中任一项所述的部件(20)。
CN202180013454.0A 2020-02-06 2021-02-01 具有含铪的镍基基材的经涂覆涡轮机部件 Pending CN115135852A (zh)

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FR2001165A FR3107080B1 (fr) 2020-02-06 2020-02-06 Piece de turbomachine revetue ayant un substrat base nickel comprenant de l'hafnium
FRFR2001165 2020-02-06
PCT/FR2021/050180 WO2021156562A1 (fr) 2020-02-06 2021-02-01 Piece de turbomachine revetue ayant un substrat base nickel comprenant de l'hafnium

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FR2557598B1 (fr) 1983-12-29 1986-11-28 Armines Alliage monocristallin a matrice a base de nickel
US7288328B2 (en) * 2004-10-29 2007-10-30 General Electric Company Superalloy article having a gamma-prime nickel aluminide coating
JP5869624B2 (ja) * 2014-06-18 2016-02-24 三菱日立パワーシステムズ株式会社 Ｎｉ基合金軟化材及びＮｉ基合金部材の製造方法
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