CN108660407B - Thermal barrier coating with prefabricated microscopic longitudinal crack structure and preparation method thereof - Google Patents
Thermal barrier coating with prefabricated microscopic longitudinal crack structure and preparation method thereof Download PDFInfo
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- 238000005516 engineering process Methods 0.000 claims abstract description 10
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- C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
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- C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
- C23C4/12—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the method of spraying
- C23C4/134—Plasma spraying
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- C—CHEMISTRY; METALLURGY
- C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
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- C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
- C23C4/02—Pretreatment of the material to be coated, e.g. for coating on selected surface areas
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- C—CHEMISTRY; METALLURGY
- C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
- C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
- C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
- C23C4/04—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the coating material
- C23C4/10—Oxides, borides, carbides, nitrides or silicides; Mixtures thereof
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Abstract
本发明公开了一种具有预制微观纵向裂纹结构的热障涂层及其制备方法。该热障涂层的陶瓷隔热层含有植入的高密度微观纵向裂纹，制备方法是利用大气等离子喷涂技术耦合干冰微粒喷射工艺制备陶瓷隔热层，通过干冰微粒喷射工艺对陶瓷熔融颗粒的在线淬火在陶瓷隔热层中植入微观纵向裂纹。与传统大气等离子喷涂和EB‑PVD(Electron beam‑physical vapor deposition)方法制备的热障涂层相比，本发明设计制备的具有预制微观纵向裂纹结构的热障涂层，既具备传统等离子喷涂制备的热障涂层的低热导率，又具有EB‑PVD技术制备的热障涂层的高应变容限，且能够在不降低涂层热冲击、隔热和CMAS(CaO‑MgO‑Al2O3‑SiO2)腐蚀抗力前提下有效释放因热应力不匹配而产生的应力，从而提高热障涂层在苛刻工况条件下的热循环服役寿命。
The invention discloses a thermal barrier coating with a prefabricated microscopic longitudinal crack structure and a preparation method thereof. The ceramic heat insulation layer of the thermal barrier coating contains implanted high-density microscopic longitudinal cracks. The preparation method is as follows: using atmospheric plasma spraying technology coupled with dry ice particle spray technology to prepare the ceramic heat insulation layer, and through the dry ice particle spray process. Quenching implants microscopic longitudinal cracks in the ceramic insulation. Compared with the thermal barrier coating prepared by traditional atmospheric plasma spraying and EB-PVD (Electron beam-physical vapor deposition) method, the thermal barrier coating with prefabricated microscopic longitudinal crack structure designed and prepared by the present invention has both the advantages of traditional plasma spraying preparation. The low thermal conductivity of the thermal barrier coating, and the high strain tolerance of the thermal barrier coating prepared by EB-PVD technology, and can not reduce the thermal shock, thermal insulation and CMAS (CaO-MgO-Al 2 O 3 -SiO 2 ) can effectively release the stress caused by thermal stress mismatch under the premise of corrosion resistance, thereby improving the thermal cycle service life of the thermal barrier coating under harsh working conditions.
Description
技术领域technical field
本发明属于材料技术领域，具体涉及到一种具有预制微观纵向裂纹结构的热障涂层及其制备方法。The invention belongs to the technical field of materials, and particularly relates to a thermal barrier coating with a prefabricated microscopic longitudinal crack structure and a preparation method thereof.
背景技术Background technique
随着航空、航天、船舰、电力及汽车技术的发展，航空发动机及燃气涡轮发动机技术的研发水平成为制约现代工业持续进步的瓶颈。当前，不断提高金属热端部件的工作温度是发展高效率、长服役寿命发动机的关键。因此，在金属热端部件表面使用具有抗高温氧化和隔热功能的热障涂层(TBCs)是提高航空和燃气涡轮发动机工作温度最有效可行的技术途径。With the development of aviation, aerospace, ship, electric power and automobile technology, the research and development level of aero-engine and gas turbine engine technology has become a bottleneck restricting the continuous progress of modern industry. At present, continuously improving the working temperature of metal hot-end components is the key to developing high-efficiency, long-service-life engines. Therefore, the use of thermal barrier coatings (TBCs) with high temperature oxidation resistance and thermal insulation functions on the surface of metal hot end components is the most effective and feasible technical way to increase the working temperature of aviation and gas turbine engines.
热障涂层(TBCs)是一种具有隔热和抗高温氧化与腐蚀防护功能的涂层系统。通过在金属基体表面沉积一定厚度且具有较低热导率的陶瓷涂层，可以提高发动机的工作温度。另一方面，TBCs可以提高金属热端部件的服役寿命和可靠性。目前，应用最广泛的TBC系统均采用双层结构：起隔热作用的表面陶瓷层(TC)和改善基体与陶瓷层物理相容性的金属粘结层(BC)。目前，制备热障涂层最常用的方法是大气等离子喷涂(APS)与电子束物理气相沉积(EB-PVD)；其中，APS制备的涂层具有典型的层状结构，具有更好的隔热性能，但TBCs在非常严苛的热力学载荷环境中服役，通常会遭遇热疲劳失效，导致涂层过早开裂、剥落等；EB-PVD制备的热障涂层具有柱状晶显微结构，该结构涂层与APS制备的涂层相比具有更好的应变容限和更长的服役寿命。然而，这种具有宏观柱状间隙或宏观纵向裂纹结构的TBCs往往具有高热导率且容易发生CMAS腐蚀失效；且EB-PVD设备昂贵、沉积效率低、涂层厚度不可控、表面清洗复杂，不适合制备结构复杂工件以及大器件上的涂层。APS由于其加工成本低、沉积效率较高、重复性好、工艺相对简单，已被广泛应用于制备航空发动机叶片、尾喷管、燃气轮机燃烧室壁、推力增强器、燃油喷管、过渡进气管段以及透平静止部件等上的热障涂层。Thermal barrier coatings (TBCs) are coating systems that provide thermal insulation and protection against high temperature oxidation and corrosion. By depositing a certain thickness of ceramic coating with low thermal conductivity on the surface of the metal substrate, the operating temperature of the engine can be increased. On the other hand, TBCs can improve the service life and reliability of metal hot-end components. At present, the most widely used TBC systems all adopt a two-layer structure: a surface ceramic layer (TC) for thermal insulation and a metallic bond layer (BC) for improving the physical compatibility between the substrate and the ceramic layer. At present, the most commonly used methods for preparing thermal barrier coatings are atmospheric plasma spraying (APS) and electron beam physical vapor deposition (EB-PVD). However, when TBCs serve in a very severe thermodynamic load environment, they usually suffer from thermal fatigue failure, resulting in premature cracking and peeling of the coating; the thermal barrier coating prepared by EB-PVD has a columnar crystal microstructure, which is a The coatings have better strain tolerance and longer service life than those prepared by APS. However, such TBCs with macroscopic columnar gaps or macroscopic longitudinal crack structures often have high thermal conductivity and are prone to CMAS corrosion failure; and EB-PVD equipment is expensive, low deposition efficiency, uncontrollable coating thickness, and complicated surface cleaning, which is not suitable for Preparation of complex workpieces and coatings on large devices. Due to its low processing cost, high deposition efficiency, good repeatability and relatively simple process, APS has been widely used in the preparation of aero-engine blades, tail nozzles, gas turbine combustion chamber walls, thrust intensifiers, fuel nozzles, transition air intakes Thermal barrier coatings on pipe sections and turbine stationary parts, etc.
鉴于APS和EB-PVD制备热障涂层各自结构的优缺点，本发明公开了一种具有微观纵向裂纹结构设计的热障涂层及其制备方法；这种结构设计的热障涂层和传统热障涂层一样，具有双层结构：金属粘结层和表面陶瓷层；这种热障涂层的陶面层中含有人为植入的微观纵向裂纹，在不显著降低涂层抗热冲击性能和隔热性能前提下提高涂层的应变容限，从而延长热障涂层的服役寿命。In view of the advantages and disadvantages of the respective structures of thermal barrier coatings prepared by APS and EB-PVD, the present invention discloses a thermal barrier coating with a microscopic longitudinal crack structure design and a preparation method thereof; Like thermal barrier coatings, it has a two-layer structure: a metal bonding layer and a surface ceramic layer; the ceramic surface layer of this thermal barrier coating contains artificially implanted microscopic longitudinal cracks, which do not significantly reduce the thermal shock resistance of the coating. On the premise of thermal barrier properties and thermal insulation properties, the strain tolerance of the coating can be improved, thereby prolonging the service life of the thermal barrier coating.
发明内容SUMMARY OF THE INVENTION
为了解决背景技术中存在的技术问题，本发明提出了一种具有微观纵向裂纹结构设计的热障涂层及其制备方法；通过涂层结构和制备方法设计，在表面陶瓷层中植入微观纵向裂纹，提高涂层的应变容限，解决APS方法制备热障涂层服役过程中过开裂、剥落等问题，延长热障涂层的服役寿命。In order to solve the technical problems existing in the background technology, the present invention proposes a thermal barrier coating with a microscopic longitudinal crack structure design and a preparation method thereof; through the design of the coating structure and preparation method, microscopic longitudinal cracks are implanted in the surface ceramic layer Cracks, improve the strain tolerance of the coating, solve the problems of excessive cracking and peeling during the service process of the thermal barrier coating prepared by the APS method, and prolong the service life of the thermal barrier coating.
为了实现上述目的，本发明通过以下技术方案来实现：In order to achieve the above object, the present invention realizes through the following technical solutions:
一种具有预制微观纵向裂纹结构的热障涂层，具有陶瓷隔热层，所述陶瓷隔热层含有高密度微观纵向裂纹，所述微观裂纹中微观纵向裂纹的比率为33％以上。A thermal barrier coating with a prefabricated microscopic longitudinal crack structure has a ceramic thermal insulation layer, the ceramic thermal insulation layer contains high-density microscopic longitudinal cracks, and the ratio of microscopic longitudinal cracks in the microscopic cracks is more than 33%.
优选地，所述的陶瓷隔热层材料包括具有低导热系数的氧化钇部分稳定氧化锆(YSZ)、锆酸镧(LZ)、铈酸澜(LC)、镁铝酸澜(LMA)。Preferably, the ceramic thermal insulation layer material includes yttrium oxide partially stabilized zirconia (YSZ), lanthanum zirconate (LZ), ceric acid lan (LC), and magnesium aluminate lan (LMA) with low thermal conductivity.
优选地，所述的陶瓷隔热层中任一微观纵向裂纹的纵向尺寸均不超过所述陶瓷隔热层总厚度，是非贯穿性裂纹。Preferably, the longitudinal dimension of any microscopic longitudinal crack in the ceramic heat insulating layer does not exceed the total thickness of the ceramic heat insulating layer, and is a non-penetrating crack.
一种具有预制微观纵向裂纹结构热障涂层的制备方法，包括以下步骤：A preparation method of thermal barrier coating with prefabricated microscopic longitudinal crack structure, comprising the following steps:
(1)预处理，采用大气等离子焰流耦合干冰微粒喷射工艺，对需要沉积热障涂层的基体或者带有金属粘结层的基体进行预热处理，其中，预热温度为60℃～100℃；(1) Pretreatment, using atmospheric plasma flame coupled with dry ice particle spraying process to preheat the substrate to be deposited thermal barrier coating or the substrate with metal bonding layer, wherein the preheating temperature is 60 ℃ ~ 100 ℃ °C;
(2)喷涂处理，通过大气等离子喷涂法耦合干冰微粒喷射工艺，将热障涂层陶瓷材料粉末沉积在步骤(1)预处理的基体或者金属粘结层上，得到含有高比例微观纵向裂纹的热障涂层。(2) Spraying treatment, through atmospheric plasma spraying method coupled with dry ice particle spraying process, the thermal barrier coating ceramic material powder is deposited on the substrate or metal bonding layer pretreated in step (1) to obtain a high proportion of microscopic longitudinal cracks. Thermal barrier coating.
优选地，步骤(1)中所述的耦合方式包括：a，大气等离子焰流预热后再采用干冰微粒喷射处理；b，干冰微粒喷射处理后再采用大气等离子焰流预热；干冰微粒喷射预处理对基体有一定的清洁作用，耦合大气等离子预热处理可以避免过冷引起‘冷凝’。Preferably, the coupling method described in step (1) includes: a, using the dry ice particle spraying after preheating the atmospheric plasma flame; b, using the atmospheric plasma flame preheating after the dry ice particle spraying; and spraying the dry ice particles Pretreatment has a certain cleaning effect on the substrate, and coupled atmospheric plasma preheating can avoid 'condensation' caused by supercooling.
优选地，步骤(2)中所述的耦合方式包括：a，大气等离子喷涂沉积后再采用干冰微粒喷射处理；b，干冰微粒喷射处理后再采用大气等离子喷涂沉积。Preferably, the coupling method described in step (2) includes: a, spraying dry ice particles after deposition by atmospheric plasma spraying; b, using atmospheric plasma spraying for deposition after spraying dry ice particles.
优选地，步骤(1)和(2)中所述的干冰微粒喷射枪与等离子喷涂枪之间的夹角为15o～45o，且干冰微粒喷射枪与涂层间的距离为20～40mm，干冰喷射流量为20～60kg/h。Preferably, the angle between the dry ice particle spray gun and the plasma spray gun described in steps (1) and (2) is 15° to 45°, and the distance between the dry ice particle spray gun and the coating is 20 to 40mm. The jet flow rate is 20-60kg/h.
与现有制备技术相比，本发明具有以下优点：Compared with the existing preparation technology, the present invention has the following advantages:
本发明提供的具有预制微观纵向裂纹结构热障涂层的制备方法，通过在大气等离子喷涂过程中耦合干冰微粒喷射工艺制备陶瓷隔热层形成热障涂层；通过干冰微粒对熔融陶瓷颗粒的淬火效应，在陶瓷层中植入微观纵向裂纹。该方法操作简单方便，在现有大气等离子喷涂过程中，在线同步完成，且干冰微粒喷射后即升华，无二次污染，经济环保。The preparation method of the thermal barrier coating with prefabricated microscopic longitudinal crack structure provided by the present invention is to prepare the ceramic thermal barrier coating by coupling the dry ice particle spraying process in the atmospheric plasma spraying process to form the thermal barrier coating; the quenching of the molten ceramic particles by the dry ice particles effect, implanting microscopic longitudinal cracks in the ceramic layer. The method is simple and convenient to operate, and in the existing atmospheric plasma spraying process, it is completed online synchronously, and the dry ice particles are sublimated after spraying, without secondary pollution, and is economical and environmentally friendly.
本发明提供的微观纵向裂纹结构设计的热障涂层，不同于宏观纵向裂纹结构的热障涂层，含有高比例的微观纵向裂纹，该热障涂层微观纵向裂纹密度的大幅增加可以有效提高涂层应变容限的同时不显著降低涂层的热冲击、隔热和CMAS腐蚀抗力等性能，有效地延长了热障涂层苛刻服役环境下的寿命，扩大了热障涂层的应用范围，使得本发明提供的热障涂层能够在航空航天、船舰电力及汽车制造等领域安全可靠应用。The thermal barrier coating with the microscopic longitudinal crack structure design provided by the present invention is different from the thermal barrier coating with the macroscopic longitudinal crack structure, and contains a high proportion of microscopic longitudinal cracks. The large increase in the microscopic longitudinal crack density of the thermal barrier coating can effectively improve the The strain tolerance of the coating does not significantly reduce the thermal shock, heat insulation and CMAS corrosion resistance of the coating, which effectively prolongs the life of the thermal barrier coating in harsh service environments and expands the application range of the thermal barrier coating. The thermal barrier coating provided by the present invention can be safely and reliably applied in the fields of aerospace, ship power, automobile manufacturing and the like.
附图说明Description of drawings
图1为本发明中预制微观纵向裂纹的热障涂层结构设计示意图，图中1代表陶瓷层；2代表粘结层；3代表基体，其中左侧图为宏观纵向裂纹或柱状结构热障涂层示意图，右侧图为预制微观纵向裂纹结构的热障涂层示意图；Figure 1 is a schematic diagram of the structural design of the thermal barrier coating with prefabricated microscopic longitudinal cracks in the present invention. In the figure, 1 represents the ceramic layer; 2 represents the bonding layer; Schematic diagram of the layers, and the diagram on the right is a schematic diagram of a thermal barrier coating with a prefabricated microscopic longitudinal crack structure;
图2为本发明实施例1中制得的具有微观纵向裂纹结构的8YSZ型热障涂层截面形貌，其中(a)为8YSZ热障涂层低倍形貌，(b)为8YSZ陶瓷面层高倍形貌；Figure 2 is the sectional morphology of the 8YSZ thermal barrier coating with a microscopic longitudinal crack structure prepared in Example 1 of the present invention, wherein (a) is the low magnification morphology of the 8YSZ thermal barrier coating, (b) is the 8YSZ ceramic surface Layer high magnification;
图3为本发明实施例2中制得的具有微观纵向裂纹结构的LMA型热障涂层截面形貌，其中(a)为LMA热障涂层低倍形貌，(b)为LMA陶瓷面层高倍形貌。3 is the cross-sectional morphology of the LMA-type thermal barrier coating with a microscopic longitudinal crack structure prepared in Example 2 of the present invention, wherein (a) is the low-magnification morphology of the LMA thermal barrier coating, and (b) is the LMA ceramic surface Layer high magnification.
具体实施方式Detailed ways
下面结合具体的实施例对本发明作进一步详细说明，实施例是对本发明的解释，并不限定本发明的保护范围。The present invention will be described in further detail below with reference to specific embodiments, which are intended to explain the present invention and do not limit the protection scope of the present invention.
实施例1Example 1
(1)通过大气等离子喷涂焰流耦合干冰微粒喷射工艺，对带有CoNiCrAlY金属粘结层的试样进行预热处理，具体地耦合方式是采用干冰微粒喷射工艺对试样进行预处理后再大气等离子喷涂焰流预热；根据大气等离子喷涂设备要求，选择等离子喷涂电压为65.0V，电流为630A，等离子喷涂距离为115mm；根据干冰微粒喷射设备要求，选择直径为3mm，长度为3～10mm的圆柱状干冰微粒，干冰流量为42kg/h，干冰微粒喷射枪与涂层间的距离为25mm；干冰喷枪与等离子喷枪之间的夹角为30°；预热温度为100℃；(1) The samples with CoNiCrAlY metal bonding layer are preheated by the atmospheric plasma spraying flame coupled with the dry ice particle spraying process. Plasma spraying flame preheating; according to the requirements of atmospheric plasma spraying equipment, the plasma spraying voltage is 65.0V, the current is 630A, and the plasma spraying distance is 115mm; according to the requirements of the dry ice particle spraying equipment, the diameter is 3mm and the length is 3~10mm. Cylindrical dry ice particles, the dry ice flow rate is 42kg/h, the distance between the dry ice particle spray gun and the coating is 25mm; the angle between the dry ice spray gun and the plasma spray gun is 30°; the preheating temperature is 100°C;
(2)通过大气等离子喷涂耦合干冰微粒喷射工艺，将粒径为15～58μm质量分数为8％Y2O3部分稳定的ZrO2(8YSZ)粉末沉积在上述预热试样上，得到含微观纵向裂纹比例为50.51％的8YSZ热障涂层；根据大气等离子喷涂设备要求，选择喷涂电压为65.0V，电流为630A，送粉气为Ar，流量3.0SLPM，等离子喷涂距离为115mm，陶瓷层总厚度为600μm；根据干冰微粒喷射设备要求，选择直径为3mm，长度为3～10mm的圆柱状干冰微粒，干冰流量为42kg/h，喷射距离为25mm；耦合方式是采用干冰微粒喷射工艺对试样预处理后再大气等离子喷涂沉积涂层，干冰喷枪与等离子喷枪之间的夹角为30°。(2) Through atmospheric plasma spraying coupled with dry ice particle spraying process, ZrO 2 (8YSZ) powder with a particle size of 15-58 μm and a mass fraction of 8% Y 2 O 3 was deposited on the above preheated sample to obtain micro 8YSZ thermal barrier coating with a longitudinal crack ratio of 50.51%; according to the requirements of atmospheric plasma spraying equipment, the spraying voltage is 65.0V, the current is 630A, the powder gas is Ar, the flow rate is 3.0SLPM, the plasma spraying distance is 115mm, and the total ceramic layer is The thickness is 600 μm; according to the requirements of the dry ice particle blasting equipment, cylindrical dry ice particles with a diameter of 3 mm and a length of 3 to 10 mm are selected, the dry ice flow rate is 42 kg/h, and the spray distance is 25 mm; the coupling method is to use the dry ice particle blasting process to spray the sample. After pretreatment, atmospheric plasma spraying is used to deposit the coating, and the angle between the dry ice spray gun and the plasma spray gun is 30°.
为了与实施例1中制得的具有微观纵向裂纹结构的8YSZ型热障涂层的热循环寿命进行比较，下面给出对比实施例1，通过传统大气等离子喷涂制备8YSZ型热障涂层。In order to compare with the thermal cycle life of the 8YSZ type thermal barrier coating with microscopic longitudinal crack structure prepared in Example 1, Comparative Example 1 is given below. The 8YSZ type thermal barrier coating was prepared by conventional atmospheric plasma spraying.
对比实施例1Comparative Example 1
采用粒径为15～58μm质量分数为8％Y2O3部分稳定的ZrO2(8YSZ)粉末作为喷涂粉末，采用传统大气等离子喷涂在带有CoNiCrAlY金属粘结层试样表面沉积8YSZ表面陶瓷层，完成热障涂层的制备；得到的8YSZ涂层含有21.92％的微观纵向裂纹；根据大气等离子喷涂设备要求，选择喷涂电压为65.0V，电流为630A，送粉气为Ar，流量3.0SLPM，喷涂距离为115mm，陶瓷层的厚度为600μm。ZrO 2 (8YSZ) powder with a particle size of 15-58 μm and a mass fraction of 8% Y 2 O 3 partially stabilized was used as the spray powder, and the 8YSZ surface ceramic layer was deposited on the surface of the sample with CoNiCrAlY metal bonding layer by traditional atmospheric plasma spraying , to complete the preparation of thermal barrier coating; the obtained 8YSZ coating contains 21.92% of microscopic longitudinal cracks; according to the requirements of atmospheric plasma spraying equipment, the spraying voltage is 65.0V, the current is 630A, the powder feeding gas is Ar, the flow rate is 3.0SLPM, The spraying distance was 115 mm, and the thickness of the ceramic layer was 600 μm.
对以上实施例1和对比例1中制备的8YSZ型热障涂层，采用自动化高温水淬疲劳试验炉进行热循环寿命测试，测试条件为：1150℃保温30min后取出，在室温下冷却18min，该过程记为一次热循环，测试共计50次热循环。热循环50次后，实施例1制得的具有预制微观纵向裂纹结构的8YSZ热障涂层仅在涂层边缘处有少量剥落，而对比例1制得的8YSZ热障涂层几乎全部剥落。For the 8YSZ-type thermal barrier coatings prepared in the above Example 1 and Comparative Example 1, the thermal cycle life test was carried out using an automated high-temperature water quenching fatigue test furnace. This process was recorded as one thermal cycle, and a total of 50 thermal cycles were tested. After 50 thermal cycles, the 8YSZ thermal barrier coating with prefabricated microscopic longitudinal crack structure prepared in Example 1 only had a small amount of peeling off at the coating edge, while the 8YSZ thermal barrier coating prepared in Comparative Example 1 almost completely peeled off.
实施例2Example 2
(1)通过大气等离子喷涂焰流耦合干冰微粒喷射工艺，对带有NiCrAlY金属粘结层试样进行预热处理，具体地耦合方式是采用大气等离子喷涂焰流预热后再干冰微粒喷射预处理；根据大气等离子喷涂设备要求，选择喷涂电压为67.2V，电流为617A，等离子喷涂距离为100mm；根据干冰微粒喷射设备要求，选择直径为3mm，长度为3～10mm的圆柱状干冰微粒，干冰流量为42kg/h，喷射距离为25mm，干冰喷枪与等离子喷枪之间的夹角为30°；预热温度为60℃。(1) The samples with NiCrAlY metal bonding layer are preheated by the atmospheric plasma spraying flame coupled with the dry ice particle spraying process. ;According to the requirements of atmospheric plasma spraying equipment, the spraying voltage is 67.2V, the current is 617A, and the plasma spraying distance is 100mm; according to the requirements of the dry ice particle spraying equipment, cylindrical dry ice particles with a diameter of 3mm and a length of 3-10mm are selected, and the dry ice flow rate is It is 42kg/h, the spray distance is 25mm, the angle between the dry ice spray gun and the plasma spray gun is 30°, and the preheating temperature is 60°C.
(2)通过大气等离子喷涂耦合干冰微粒喷射工艺，将粒径为32～125μm的LaMgAl11O19(LMA)粉末沉积在上述预热试样上，得到含微观纵向裂纹比例为46.84％的LMA热障涂层；根据大气等离子喷涂设备要求，选择喷涂电压为67.2V，电流为617A，送粉气为Ar，流量2.8NLPM，送粉率为15g/min，喷涂距离为100mm，陶瓷层的厚度为150μm；根据干冰微粒喷射设备要求，选择直径为3mm，长度为3-10mm的圆柱状干冰微粒，干冰流量为42kg/h，喷射距离为25mm；耦合方式是采用大气等离子喷涂沉积后再干冰微粒喷射处理，干冰喷枪与等离子喷枪之间的夹角为30°。(2) LaMgAl 11 O 19 (LMA) powder with a particle size of 32-125 μm was deposited on the above-mentioned preheated sample by atmospheric plasma spraying coupled with dry ice particle spraying technology, and LMA thermal cracks with a proportion of 46.84% of microscopic longitudinal cracks were obtained. Barrier coating; according to the requirements of atmospheric plasma spraying equipment, the spraying voltage is 67.2V, the current is 617A, the powder feeding gas is Ar, the flow rate is 2.8NLPM, the powder feeding rate is 15g/min, the spraying distance is 100mm, and the thickness of the ceramic layer is 150μm; according to the requirements of dry ice particle spraying equipment, select cylindrical dry ice particles with a diameter of 3mm and a length of 3-10mm, the dry ice flow rate is 42kg/h, and the spray distance is 25mm; the coupling method is to use atmospheric plasma spray deposition and then dry ice particles spray For processing, the angle between the dry ice spray gun and the plasma spray gun is 30°.
为了与实施例2中制得的具有微观纵向裂纹结构的LMA型热障涂层的热循环寿命进行比较，下面给出对比实施例2，通过传统大气等离子喷涂制备LMA型热障涂层。In order to compare with the thermal cycle life of the LMA-type thermal barrier coating with the microscopic longitudinal crack structure prepared in Example 2, Comparative Example 2 is given below, and the LMA-type thermal barrier coating was prepared by conventional atmospheric plasma spraying.
对比实施例2Comparative Example 2
采用粒径为32～125μm的LMA粉末作为喷涂粉末，采用传统大气等离子喷涂在带有NiCrAlY金属粘结层试样表面沉积LMA表面陶瓷层，完成热障涂层的制备；得到的LMA涂层含有33.97％的微观纵向裂纹；根据大气等离子喷涂设备要求，选择喷涂电压为67.2V，电流为617A，送粉气为Ar，流量2.8NLPM，送粉率为15g/min，喷涂距离为100mm，陶瓷层的厚度为150μm。The LMA powder with a particle size of 32-125 μm was used as the spray powder, and the LMA surface ceramic layer was deposited on the surface of the sample with NiCrAlY metal bonding layer by traditional atmospheric plasma spraying to complete the preparation of the thermal barrier coating; the obtained LMA coating contains 33.97% microscopic longitudinal cracks; according to the requirements of atmospheric plasma spraying equipment, the spraying voltage is 67.2V, the current is 617A, the powder feeding gas is Ar, the flow rate is 2.8NLPM, the powder feeding rate is 15g/min, the spraying distance is 100mm, and the ceramic layer is The thickness is 150 μm.
对以上实施例2和对比例2中制备的LMA型热障涂层，采用高温管式炉进行热循环寿命测试，测试条件为：1100℃保温34min后取出，在室温下空气冷却2min，该过程记为一次热循环，记涂层剥落面积为10％左右时的热循环次数为热循环寿命。实施例2制得的具有预制微观纵向裂纹结构的LMA热障涂层热循环寿命为34次，而对比例2制得的LMA热障涂层热循环寿命为28次。For the LMA-type thermal barrier coatings prepared in the above Example 2 and Comparative Example 2, the thermal cycle life test was carried out using a high-temperature tube furnace. The test conditions were: 1100 ° C for 34 minutes and then take out, and air-cooled at room temperature for 2 minutes. This process Denote it as one thermal cycle, and denote the number of thermal cycles when the coating peeling area is about 10% as the thermal cycle life. The thermal cycle life of the LMA thermal barrier coating with the prefabricated microscopic longitudinal crack structure prepared in Example 2 was 34 times, while the thermal cycle life of the LMA thermal barrier coating prepared in Comparative Example 2 was 28 times.
在以上实施例1和对比例1以及实施例2和对比例2中，利用本发明中大气等离子喷涂耦合干冰微粒喷射工艺制备的具有预制微观纵向裂纹结构的热障涂层具有更高的热循环寿命。In the above Example 1 and Comparative Example 1 and Example 2 and Comparative Example 2, the thermal barrier coating with the prefabricated microscopic longitudinal crack structure prepared by the atmospheric plasma spraying coupled with the dry ice particle spraying process in the present invention has a higher thermal cycle. life.
与传统大气等离子喷涂和EB-PVD(Electron beam-physical vapor deposition)方法制备的热障涂层相比，本发明设计制备的具有预制微观纵向裂纹结构的热障涂层，既具备传统等离子喷涂制备的热障涂层的低热导率，又具有EB-PVD技术制备的热障涂层的高应变容限，且能够在不降低涂层热冲击、隔热和CMAS(CaO-MgO-Al2O3-SiO2)腐蚀抗力前提下有效释放因热应力不匹配而产生的应力，从而提高热障涂层在苛刻工况条件下的热循环服役寿命。Compared with the thermal barrier coating prepared by traditional atmospheric plasma spraying and EB-PVD (Electron beam-physical vapor deposition) methods, the thermal barrier coating with prefabricated microscopic longitudinal crack structure designed and prepared in the present invention has both the advantages of traditional plasma spraying preparation. The low thermal conductivity of the thermal barrier coating, and the high strain tolerance of the thermal barrier coating prepared by EB-PVD technology, and can not reduce the thermal shock, thermal insulation and CMAS (CaO-MgO-Al 2 O 3 -SiO 2 ) can effectively release the stress caused by thermal stress mismatch under the premise of corrosion resistance, thereby improving the thermal cycle service life of the thermal barrier coating under harsh working conditions.
最后所应当说明的是，以上实施例仅用以说明本发明的技术方案而非对本发明保护范围的限制，尽管参照较佳实施例对本发明作了详细说明，本领域的普通技术人员应当理解，可以对本发明的技术方案进行修改或者等同替换，而不脱离本发明技术方案的实质和范围。Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention and not to limit the protection scope of the present invention. Although the present invention is described in detail with reference to the preferred embodiments, those of ordinary skill in the art should understand that, The technical solutions of the present invention may be modified or equivalently replaced without departing from the spirit and scope of the technical solutions of the present invention.
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