CN113929482B - A kind of ceramic matrix composite turbine guide vane and preparation method thereof - Google Patents
A kind of ceramic matrix composite turbine guide vane and preparation method thereofDownload PDFInfo
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- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
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- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
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Abstract
Translated fromChinese
Description
Translated fromChinese技术领域technical field
本发明涉及燃气涡轮发动机制造技术领域，具体涉及一种陶瓷基复合材料涡轮导向叶片及其制备方法。The invention relates to the technical field of gas turbine engine manufacturing, in particular to a ceramic matrix composite material turbine guide vane and a preparation method thereof.
背景技术Background technique
在航空发动机和燃气轮机等燃气涡轮发动机结构中，涡轮系统的作用是将高温燃气中的部分热能和势能转换成机械功，驱动压气机和附件工作，涡轮系统是燃气涡轮发动机中热负荷和动力负荷最大的系统，其特点是输出功率大、使用温度高、重量要求轻、结构尺寸小，高压涡轮进口处的导向叶片是涡轮系统中工作温度最高的部件，其作用是将高温燃气流部分热能转变为动能的同时，将燃气流以一定的方向流出，满足工作涡轮所要求的燃气流量和进口方向。目前，发动机涡轮导向叶片常用的高温合金材料存在耐热温度不高于1100℃、重量大等问题，而能够耐较高温度的碳纤维增强碳基体复合材料又存在高温易氧化的缺点。陶瓷基复合材料密度仅为高温合金的1/3-1/4、耐热温度比高温合金高150-350℃、耐酸碱腐蚀、强韧性高，同时，陶瓷基复合材料在高温燃气环境中反应所生成的氧化物保护膜能够封堵材料表面的裂纹和孔隙，阻止外界氧向材料内部扩散，从而保证构件的高温稳定性和长时使用寿命，因此，陶瓷基复合材料已被国内外公认为是新一代航空发动机热防护构件的首选材料之一。In gas turbine engine structures such as aero-engines and gas turbines, the function of the turbine system is to convert part of the thermal energy and potential energy in the high-temperature gas into mechanical work to drive the compressor and accessories to work. The turbine system is the heat load and power load in the gas turbine engine. The largest system is characterized by high output power, high operating temperature, light weight and small structure size. The guide vane at the inlet of the high-pressure turbine is the component with the highest working temperature in the turbine system, and its function is to convert part of the thermal energy of the high-temperature gas flow. At the same time as kinetic energy, the gas flow flows out in a certain direction to meet the gas flow and inlet direction required by the working turbine. At present, the commonly used superalloy materials for engine turbine guide blades have problems such as heat resistance temperature not higher than 1100 ° C and heavy weight, while carbon fiber reinforced carbon matrix composite materials that can withstand higher temperatures have the disadvantage of being easily oxidized at high temperature. The density of ceramic matrix composites is only 1/3-1/4 of that of superalloys, the heat-resistant temperature is 150-350 °C higher than that of superalloys, acid and alkali corrosion resistance, and high toughness. The oxide protective film generated by the reaction can block the cracks and pores on the surface of the material and prevent the diffusion of external oxygen into the material, thereby ensuring the high temperature stability and long service life of the component. Therefore, ceramic matrix composites have been recognized at home and abroad. It is one of the preferred materials for the new generation of aero-engine thermal protection components.
以陶瓷基复合材料作为结构主体材料进行导向叶片设计时，通常采用分体式结构方案，即分别制备出叶片的叶身和缘板，随后通过拼接、组装、后沉积等方式进行整体装配，尽管此方法能够实现叶片的制备，但叶身和缘板之间的连接可靠性存在较大风险，叶片在发动机长时间高温、振动工作环境下，可能在连接部位发生损坏，并导致灾难性后果。When designing guide vanes with ceramic matrix composites as the main structural material, a split structure scheme is usually adopted, that is, the blade body and edge plate of the blade are prepared separately, and then the overall assembly is performed by splicing, assembly, post-deposition, etc. The method can realize the preparation of the blade, but there is a great risk in the reliability of the connection between the blade body and the edge plate. Under the long-term high temperature and vibration working environment of the engine, the blade may be damaged at the connection part and lead to catastrophic consequences.
发明内容SUMMARY OF THE INVENTION
为了解决上述技术问题，本发明的目的是提供一种陶瓷基复合材料涡轮导向叶片及其制备方法，以解决现有技术制备涡轮导向叶片时，叶身和缘板之间的连接可靠性存在较大风险的问题。In order to solve the above technical problems, the purpose of the present invention is to provide a ceramic matrix composite turbine guide vane and a preparation method thereof, so as to solve the problem that the connection reliability between the blade body and the edge plate is relatively low when the turbine guide vane is prepared in the prior art. big risk issues.
本发明解决上述技术问题的技术方案如下：提供一种陶瓷基复合材料涡轮导向叶片，所述涡轮导向叶片的材质为陶瓷基复合材料，且涡轮导向叶片的叶身和缘板为一体化成型。The technical solution of the present invention to solve the above technical problems is as follows: a ceramic-based composite turbine guide vane is provided, wherein the material of the turbine guide vane is a ceramic-based composite material, and the blade body and the edge plate of the turbine guide vane are integrally formed.
本发明的有益效果为：涡轮导向叶片的叶身和缘板为一体化成型，避免了结构单元之间的拼接，使得叶身与缘板之间的连接可靠性大大增强。The beneficial effects of the invention are that the blade body and the edge plate of the turbine guide vane are integrally formed, which avoids splicing between structural units, and greatly enhances the connection reliability between the blade body and the edge plate.
在上述技术方案的基础上，本发明还可以做如下改进：On the basis of above-mentioned technical scheme, the present invention can also do following improvement:
进一步，陶瓷基复合材料的增强体为碳纤维和/或碳化硅纤维，基体为碳化硅。Further, the reinforcement of the ceramic matrix composite material is carbon fiber and/or silicon carbide fiber, and the matrix is silicon carbide.
本发明还提供上述陶瓷基复合材料涡轮导向叶片的制备方法，包括以下步骤：The present invention also provides a method for preparing the above-mentioned ceramic matrix composite turbine guide vane, comprising the following steps:
(1)以涡轮导向叶片的内腔型面为参考，用石墨制备内型模具，内型模具上具有若干与型面垂直的通气孔；(1) Taking the inner cavity profile of the turbine guide vane as a reference, an inner mold is prepared with graphite, and the inner mold has a number of ventilation holes perpendicular to the profile;
(2)将编织纤维布缠绕在内型模具的外表面，然后采用与编织纤维布相同材料的缝合线进行缝合，缝合完毕的缠绕编织纤维布即为叶身预制体，再分别在叶身预制体上距离两端5-10mm处，进行切口处理，切口方向与叶身预制体的纵向平行，切口长度为10-50mm；(2) Wind the woven fiber cloth on the outer surface of the inner mold, and then stitch with the same material as the woven fiber cloth. The body is 5-10mm away from both ends, and the incision is processed, the incision direction is parallel to the longitudinal direction of the blade body prefab, and the incision length is 10-50mm;
(3)采用与叶身预制体相同材料的编织纤维布制备4片相同的板状预制体，并在相应的叶身位置处开孔，孔的形状与叶身预制体截面相同；(3) 4 pieces of identical plate-like preforms are prepared by using the woven fiber cloth of the same material as the airfoil preform, and holes are opened at the corresponding airfoil positions, and the shape of the holes is the same as the cross section of the airfoil preform;
(4)将4片板状预制体沿开孔穿入叶身预制体，其中2片位于叶身预制体上部切口的两侧，另外2片位于叶身预制体下部切口的两侧，然后分别将叶身预制体切口处的编织纤维布沿叶身外型面翻出，并将翻边夹在板状预制体之间，再用与叶身预制体相同材料的缝合线分别将2片板状预制体和夹在中间的翻边缝合为一体，最后再利用内型模具，将叶身预制体和板状预制体固定，完成定型；(4) 4 pieces of plate-like preforms are inserted into the airfoil preform along the opening, 2 of which are located on both sides of the upper incision of the airfoil preform, and the other 2 are located on both sides of the lower incision of the airfoil preform, and then respectively Turn out the woven fiber cloth at the incision of the airfoil preform along the outer surface of the airfoil, and sandwich the flanging between the plate preforms, and then use the suture of the same material as the airfoil preform to separate the two plates. The airfoil preform and the flange sandwiched in the middle are sewn together, and finally the inner mold is used to fix the blade body preform and the plate preform to complete the final shape;
(5)在定型后的叶身预制体和板状预制体表面依次沉积界面层和碳化硅陶瓷基体，去除内型模具后，得到陶瓷基复合材料涡轮导向叶片坯料；(5) depositing an interface layer and a silicon carbide ceramic matrix on the surfaces of the shaped airfoil preform and the plate preform in turn, and removing the inner mold to obtain a ceramic matrix composite turbine guide vane blank;
(6)将陶瓷基复合材料涡轮导向叶片坯料加工至设计尺寸，然后继续在其表面沉积碳化硅，进行损伤修复，得到陶瓷基复合材料涡轮导向叶片。(6) Process the ceramic matrix composite turbine guide vane blank to the design size, and then continue to deposit silicon carbide on its surface to repair the damage to obtain the ceramic matrix composite turbine guide vane.
进一步，步骤(1)中通气孔直径为2-5mm。Further, in step (1), the diameter of the vent hole is 2-5mm.
进一步，步骤(1)中石墨为电极石墨或高纯石墨。Further, in step (1), the graphite is electrode graphite or high-purity graphite.
进一步，步骤(2)中编织纤维布原材料为碳纤维和/或碳化硅纤维。Further, in step (2), the raw material of the woven fiber cloth is carbon fiber and/or silicon carbide fiber.
进一步，步骤(2)中编织方法为二维平纹编织、二维缎纹编织、二维斜纹编织或2.5维编织。Further, the weaving method in step (2) is two-dimensional plain weave, two-dimensional satin weave, two-dimensional twill weave or 2.5-dimensional weave.
进一步，步骤(2)中，切口间距为10-13mm.。Further, in step (2), the incision spacing is 10-13mm.
进一步，步骤(3)中板状预制体的厚度为缘板设计厚度的0.3-0.5倍。Further, in step (3), the thickness of the plate-shaped preform is 0.3-0.5 times the design thickness of the edge plate.
进一步，步骤(5)中沉积界面层和碳化硅陶瓷基体是利用化学气相沉积法进行沉积。Further, the deposition of the interface layer and the silicon carbide ceramic substrate in step (5) is performed by chemical vapor deposition.
进一步，步骤(5)中界面层为氮化硼界面层。Further, in step (5), the interface layer is a boron nitride interface layer.
进一步，氮化硼界面层的制备过程为：于压力为50-1000Pa条件下，升温至650-1000℃，保温1-2h后，通入氩气、氢气、氨气和三氯化硼气体的混合气体，沉积15-35h后，继续保温1-2h，降温至室温；其中，氩气、氢气、氨气和三氯化硼气体的流量比为1：1-3：2-8：2-8。Further, the preparation process of the boron nitride interface layer is as follows: under the condition of a pressure of 50-1000Pa, the temperature is raised to 650-1000°C, and after heat preservation for 1-2h, a mixture of argon, hydrogen, ammonia and boron trichloride gas is introduced. The mixed gas is deposited for 15-35h, then kept for 1-2h and cooled to room temperature; wherein, the flow ratio of argon, hydrogen, ammonia and boron trichloride gas is 1:1-3:2-8:2- 8.
进一步，氮化硼界面层制备过程执行1-3次。Further, the boron nitride interface layer preparation process is performed 1-3 times.
进一步，碳化硅陶瓷基体的制备过程为：于压力为200-5000Pa的条件下，升温至900-1200℃，保温1-2h后，通入三氯甲基硅烷、氢气和氩气的混合气体，沉积30-80h后，继续保温2h，降温至室温；此制备过程执行4-8次。Further, the preparation process of the silicon carbide ceramic substrate is as follows: under the condition of a pressure of 200-5000Pa, the temperature is raised to 900-1200°C, and after 1-2h heat preservation, a mixed gas of trichloromethylsilane, hydrogen and argon is introduced, After 30-80 hours of deposition, the temperature was kept for 2 hours, and the temperature was lowered to room temperature; this preparation process was performed 4-8 times.
进一步，三氯甲基硅烷∶氢气∶氩气的流量比为1：5-15：10-20。Further, the flow ratio of trichloromethylsilane:hydrogen:argon is 1:5-15:10-20.
进一步，步骤(6)中加工是利用机械或激光加工。Further, the processing in step (6) is by mechanical or laser processing.
进一步，步骤(6)中沉积碳化硅的过程为：于压力为200-5000Pa的条件下，升温至900-1200℃，保温1-2h后，通入三氯甲基硅烷、氢气和氩气的混合气体，沉积30-80h后，继续保温2h，降温至室温；此制备过程执行1-3次。Further, the process of depositing silicon carbide in the step (6) is as follows: under the condition of a pressure of 200-5000Pa, the temperature is raised to 900-1200°C, and after being kept for 1-2h, a mixture of trichloromethylsilane, hydrogen and argon is introduced. The mixed gas is deposited for 30-80h, then kept for 2h and cooled to room temperature; this preparation process is performed 1-3 times.
本发明具有以下有益效果：The present invention has the following beneficial effects:
一、本发明利用纤维预制体本身的柔性特征，通过在叶身预制体上原位开槽的方式获得叶身两端的翻边结构，并与缘板预制体进行一体化缝合成型，并在后续工艺过程中完成同步致密化，这种技术方案避免了多个零件的组装工序，提升了构件的整体性。此外，通过缝合纤维的加强作用，可提升叶身与缘板之间的连接强度约20-35％，提高了构件的结构可靠性。1. The present invention utilizes the flexible characteristics of the fiber preform itself, obtains the flanging structure at both ends of the airfoil by in-situ grooving on the airfoil preform, and performs integrated suturing with the edge plate preform, and in the follow-up Simultaneous densification is completed during the process. This technical solution avoids the assembly process of multiple parts and improves the integrity of the components. In addition, through the reinforcing effect of the stitched fibers, the connection strength between the blade body and the edge plate can be increased by about 20-35%, and the structural reliability of the component is improved.
二、本发明方法可以适用于单联和多联导向叶片的制备，而且是一种近净尺寸制备方法，其适用范围广，可为陶瓷基复合材料涡轮导向叶片的批量化生产提供支撑。2. The method of the present invention can be applied to the preparation of single and multiple guide vanes, and is a near-net size preparation method, which has a wide range of applications and can provide support for the mass production of ceramic matrix composite turbine guide vanes.
附图说明Description of drawings
图1为本发明叶身预制体的切口示意图；Fig. 1 is the cutout schematic diagram of the blade body preform of the present invention;
图2为本发明板状预制体示意图；Fig. 2 is the schematic diagram of the plate-shaped preform of the present invention;
图3为本发明叶身预制体的翻边示意图；Fig. 3 is the flanging schematic diagram of the blade body preform of the present invention;
图4为实施例1中叶身预制体和板状预制体定型示意图；4 is a schematic diagram of the shaping of the airfoil preform and the plate preform in Example 1;
图5为实施例1制备的陶瓷基复合材料涡轮导向叶片的实物照片。FIG. 5 is a real photo of the ceramic matrix composite turbine guide vane prepared in Example 1. FIG.
其中，1、内型模具；2、叶身预制体；3、切口；4、板状预制体；5、开孔；6、翻边。Among them, 1. inner mold; 2. airfoil prefab; 3. incision; 4. plate prefab; 5. opening; 6. flanging.
具体实施方式Detailed ways
以下结合附图对本发明的原理和特征进行描述，所举实例只用于解释本发明，并非用于限定本发明的范围。实施例中未注明具体条件者，按照常规条件或制造商建议的条件进行。所用试剂或仪器未注明生产厂商者，均为可以通过市售购买获得的常规产品。The principles and features of the present invention will be described below with reference to the accompanying drawings. The examples are only used to explain the present invention, but not to limit the scope of the present invention. If the specific conditions are not indicated in the examples, it is carried out according to the conventional conditions or the conditions suggested by the manufacturer. The reagents or instruments used without the manufacturer's indication are conventional products that can be purchased from the market.
实施例1：Example 1:
一种陶瓷基复合材料涡轮导向叶片，其制备方法包括以下步骤：A ceramic matrix composite turbine guide vane, the preparation method of which comprises the following steps:
(1)以涡轮导向叶片的内腔型面为参考，用电极石墨制备内型模具1，内型模具1上有若干与型面垂直的直径为3mm的通气孔；(1) Taking the inner cavity profile of the turbine guide vane as a reference, an
(2)将二维平纹编织碳纤维布缠绕在内型模具1的外表面，然后采用碳纤维缝合线进行缝合，缝合完毕的缠绕碳纤维布即为叶身预制体2，再分别在叶身预制体2上距离两端8mm处，进行切口处理，切口3方向与叶身预制体2的纵向平行，切口3长度为40mm，切口3间距为12mm；(2) The two-dimensional plain weave carbon fiber cloth is wound on the outer surface of the
(3)将二维平纹编织碳纤维布叠层缝合，制备4片相同的板状预制体4，其每片厚度为缘板设计厚度的0.35倍，然后在相应的叶身位置处，采用裁切的方式进行开孔，开孔5的形状与叶身截面相同；(3) Lay and sew the two-dimensional plain weave carbon fiber cloth to prepare 4 identical plate-shaped
(4)沿步骤(3)中所述开孔5，将4片板状预制体4穿入叶身预制体2，其中2片位于叶身预制体2上部切口3的两侧，另外2片位于叶身预制体2下部切口3的两侧，然后分别将叶身预制体2切口3处的二维平纹编织碳纤维布沿叶身外型面翻出，并将翻边6夹在板状预制体4之间，再用碳纤维缝合线分别将2片板状预制体4和夹在中间的翻边6缝合为一体；再利用内型模具1，将叶身预制体2和板状预制体4固定，完成定型；(4) Along the
(5)将在定型后的叶身预制体2、板状预制体4和内型模具1一同放入化学气相沉积炉内，依次在预制体表面沉积氮化硼界面层和碳化硅陶瓷基体，去除内型模具1后，得到陶瓷基复合材料涡轮导向叶片坯料；(5) Put the shaped
氮化硼界面层的制备过程为：于压力为550Pa的条件下，升温至680℃，保温2h后，通入氩气、氢气、氨气和三氯化硼气体的混合气体，氩气、氢气、氨气和三氯化硼气体的流量比为1：1-3：2-8：2-8，沉积30h后，继续保温2h，降温至室温；此步骤循环执行2次；The preparation process of the boron nitride interface layer is as follows: under the condition of a pressure of 550Pa, the temperature is raised to 680°C, and after holding for 2 hours, a mixed gas of argon, hydrogen, ammonia and boron trichloride gas is introduced, argon, hydrogen , the flow ratio of ammonia gas and boron trichloride gas is 1:1-3:2-8:2-8, after 30h of deposition, continue to keep warm for 2h, and cool down to room temperature; this step is performed 2 times in a cycle;
碳化硅陶瓷基体的制备过程为：于压力为1200a的条件下，升温至1050℃，保温2h后，通入三氯甲基硅烷、氢气和氩气的混合气体，三氯甲基硅烷∶氢气∶氩气的流量比为1：12：15，沉积72h后，继续保温2h，降温至室温；此步骤循环执行7次；The preparation process of the silicon carbide ceramic substrate is as follows: under the condition of a pressure of 1200a, the temperature is raised to 1050°C, and after holding for 2h, a mixed gas of trichloromethylsilane, hydrogen and argon is introduced, trichloromethylsilane: hydrogen: The flow ratio of argon is 1:12:15, after 72h of deposition, the temperature is continued for 2h, and the temperature is lowered to room temperature; this step is repeated 7 times;
(6)将陶瓷基复合材料涡轮导向叶片坯料利用机械或激光加工至设计尺寸，得到陶瓷基复合材料涡轮导向叶片半成品，然后将半成品置于碳化硅化学气相沉积炉内，将碳化硅陶瓷沉积于陶瓷基复合材料涡轮导向叶片半成品的所有加工面(制备过程与步骤(5)中碳化硅陶瓷基体的制备过程相同)，进行损伤修复，循环沉积2次，得到陶瓷基复合材料涡轮导向叶片。(6) The ceramic matrix composite turbine guide vane blank is machined to the design size by mechanical or laser processing to obtain a semi-finished ceramic matrix composite turbine guide vane, and then the semi-finished product is placed in a silicon carbide chemical vapor deposition furnace, and the silicon carbide ceramic is deposited on the All machined surfaces of the semi-finished ceramic matrix composite turbine guide blade (the preparation process is the same as the preparation process of the silicon carbide ceramic matrix in step (5)), carry out damage repair, and cycle deposition twice to obtain the ceramic matrix composite turbine guide blade.
实施例2：Example 2:
一种陶瓷基复合材料涡轮导向叶片，其制备方法包括以下步骤：A ceramic matrix composite turbine guide vane, the preparation method of which comprises the following steps:
(1)以涡轮导向叶片的内腔型面为参考，用电极石墨制备内型模具1，内型模具1上有若干与型面垂直的直径为2mm的通气孔；(1) Taking the inner cavity profile of the turbine guide vane as a reference, the
(2)将二维缎纹编织碳化硅纤维布缠绕在内型模具1的外表面，然后采用碳化硅纤维缝合线进行缝合，缝合完毕的缠绕碳化硅纤维布即为叶身预制体2，再分别在叶身预制体2上距离两端5mm处，进行切口处理，切口3方向与叶身预制体2的纵向平行，切口3长度为10mm，切口3间距为10mm；(2) Winding the two-dimensional satin weave silicon carbide fiber cloth on the outer surface of the
(3)将二维缎纹编织碳化硅纤维布叠层缝合，制备4片相同的板状预制体4，其每片厚度为缘板设计厚度的0.3倍，然后在相应的叶身位置处，采用裁切的方式进行开孔，开孔5的形状与叶身截面相同；(3) The two-dimensional satin woven silicon carbide fiber cloth is laminated and sewed to prepare four identical plate-shaped
(4)沿步骤(3)中所述开孔5，将4片板状预制体4穿入叶身预制体2，其中2片位于叶身预制体2上部切口3的两侧，另外2片位于叶身预制体2下部切口3的两侧，然后分别将叶身预制体2切口3处的二维缎纹编织碳化硅纤维布沿叶身外型面翻出，并将翻边6夹在板状预制体4之间，再用碳化硅纤维缝合线分别将2片板状预制体4和夹在中间的翻边6缝合为一体；再利用内型模具1，将叶身预制体2和板状预制体4固定，完成定型；(4) Along the
(5)将在定型后的叶身预制体2、板状预制体4和内型模具1一同放入化学气相沉积炉内，依次在预制体表面沉积氮化硼界面层和碳化硅陶瓷基体，去除内型模具1后，得到陶瓷基复合材料涡轮导向叶片坯料；(5) Put the shaped
氮化硼界面层的制备过程为：于压力为50Pa的条件下，升温至650℃，保温2h后，依次通入氩气、氢气、氨气和三氯化硼气体，氩气、氢气、氨气和三氯化硼气体的流量比为1：1-3：2-8：2-8，沉积35h后，继续保温2h，降温至室温；此步骤循环执行3次；The preparation process of the boron nitride interface layer is as follows: under the condition of a pressure of 50Pa, the temperature is raised to 650°C, and after holding for 2h, argon, hydrogen, ammonia and boron trichloride gas are introduced in sequence, argon, hydrogen, ammonia The flow ratio of gas and boron trichloride gas is 1: 1-3: 2-8: 2-8, after 35 hours of deposition, continue to keep warm for 2 hours, and cool down to room temperature; this step is performed 3 times in a cycle;
碳化硅陶瓷基体的制备过程为：于压力为200Pa的条件下，升温至900℃，保温2h后，通入三氯甲基硅烷、氢气和氩气的混合气体，三氯甲基硅烷∶氢气∶氩气的流量比为1：5：10，沉积80h后，继续保温2h，降温至室温；此步骤循环执行8次；The preparation process of the silicon carbide ceramic substrate is as follows: under the condition of a pressure of 200Pa, the temperature is raised to 900°C, and after holding for 2 hours, a mixed gas of trichloromethylsilane, hydrogen and argon is introduced, trichloromethylsilane: hydrogen: The flow ratio of argon is 1:5:10, after 80h of deposition, the temperature is continued for 2h, and the temperature is lowered to room temperature; this step is repeated 8 times;
(6)将陶瓷基复合材料涡轮导向叶片坯料利用机械或激光加工至设计尺寸，得到陶瓷基复合材料涡轮导向叶片半成品，然后将半成品置于碳化硅化学气相沉积炉内，将碳化硅陶瓷沉积于陶瓷基复合材料涡轮导向叶片半成品的所有加工面(制备过程与步骤(5)中碳化硅陶瓷基体的制备过程相同)，进行损伤修复，循环沉积3次，得到陶瓷基复合材料涡轮导向叶片。(6) The ceramic matrix composite turbine guide vane blank is machined to the design size by mechanical or laser processing to obtain a semi-finished ceramic matrix composite turbine guide vane, and then the semi-finished product is placed in a silicon carbide chemical vapor deposition furnace, and the silicon carbide ceramic is deposited on the All machined surfaces of the semi-finished ceramic matrix composite turbine guide blade (the preparation process is the same as the preparation process of the silicon carbide ceramic matrix in step (5)), carry out damage repair, and
实施例3：Example 3:
一种陶瓷基复合材料涡轮导向叶片，其制备方法包括以下步骤：A ceramic matrix composite turbine guide vane, the preparation method of which comprises the following steps:
(1)以涡轮导向叶片的内腔型面为参考，用电极石墨制备内型模具1，内型模具1上有若干与型面垂直的直径为5mm的通气孔；(1) Taking the inner cavity profile of the turbine guide vane as a reference, the
(2)将二维斜纹编织碳纤维布缠绕在内型模具1的外表面，然后采用碳纤维缝合线进行缝合，缝合完毕的缠绕碳纤维布即为叶身预制体2，再分别在叶身预制体2上距离两端10mm处，进行切口处理，切口3方向与叶身预制体2的纵向平行，切口3长度为50mm，切口3间距为13mm；(2) Winding the two-dimensional twill weave carbon fiber cloth on the outer surface of the
(3)将二维斜纹编织碳纤维布叠层缝合，制备4片相同的板状预制体4，其每片厚度为缘板设计厚度的0.5倍，然后在相应的叶身位置处，采用裁切的方式进行开孔，开孔5的形状与叶身截面相同；(3) Lay and sew the two-dimensional twill weave carbon fiber cloth to prepare 4 identical plate-shaped
(4)沿步骤(3)中所述开孔5，将4片板状预制体4穿入叶身预制体2，其中2片位于叶身预制体2上部切口3的两侧，另外2片位于叶身预制体2下部切口3的两侧，然后分别将叶身预制体2切口3处的编织纤维布沿叶身外型面翻出，并将翻边6夹在板状预制体4之间，再用碳纤维缝合线分别将2片板状预制体4和夹在中间的翻边6缝合为一体；再利用内型模具1，将叶身预制体2和板状预制体4固定，完成定型；(4) Along the
(5)将在定型后的叶身预制体2、板状预制体4和内型模具1一同放入化学气相沉积炉内，依次在预制体表面沉积氮化硼界面层和碳化硅陶瓷基体，去除内型模具1后，得到陶瓷基复合材料涡轮导向叶片坯料；(5) Put the shaped
氮化硼界面层的制备过程为：于压力为1000Pa的条件下，升温至1000℃，保温1h后，依次通入氩气、氢气、氨气和三氯化硼气体，氩气、氢气、氨气和三氯化硼气体的流量比为1：1-3：2-8：2-8，沉积15h后，继续保温1h，降温至室温；The preparation process of the boron nitride interface layer is as follows: under the condition of a pressure of 1000Pa, the temperature is raised to 1000°C, and after 1 h of heat preservation, argon, hydrogen, ammonia and boron trichloride gas are introduced in sequence, argon, hydrogen, ammonia The flow ratio of gas and boron trichloride gas is 1:1-3:2-8:2-8, after 15h of deposition, continue to keep warm for 1h, and cool down to room temperature;
碳化硅陶瓷基体的制备过程为：于压力为5000Pa的条件下，升温至1200℃，保温1h后，通入三氯甲基硅烷、氢气和氩气的混合气体，三氯甲基硅烷∶氢气∶氩气的流量比为1：15：20，沉积30h后，继续保温1h，降温至室温；此步骤循环执行4次；The preparation process of the silicon carbide ceramic substrate is as follows: under the condition of a pressure of 5000Pa, the temperature is raised to 1200°C, and after 1 h of heat preservation, a mixed gas of trichloromethylsilane, hydrogen and argon is introduced, trichloromethylsilane: hydrogen: The flow ratio of argon is 1:15:20, after 30h of deposition, the temperature is continued for 1h, and the temperature is lowered to room temperature; this step is repeated 4 times;
(6)将陶瓷基复合材料涡轮导向叶片坯料利用机械或激光加工至设计尺寸，得到陶瓷基复合材料涡轮导向叶片半成品，然后将半成品置于碳化硅化学气相沉积炉内，将碳化硅陶瓷沉积于陶瓷基复合材料涡轮导向叶片半成品的所有加工面(制备过程与步骤(5)中碳化硅陶瓷基体的制备过程相同)，进行损伤修复，得到陶瓷基复合材料涡轮导向叶片。(6) The ceramic matrix composite turbine guide vane blank is machined to the design size by mechanical or laser processing to obtain a semi-finished ceramic matrix composite turbine guide vane, and then the semi-finished product is placed in a silicon carbide chemical vapor deposition furnace, and the silicon carbide ceramic is deposited on the All machined surfaces of the semi-finished ceramic matrix composite turbine guide vane (the preparation process is the same as the preparation process of the silicon carbide ceramic matrix in step (5)) are damaged and repaired to obtain the ceramic matrix composite turbine guide vane.
效果验证Effect verification
对实施例1-3制备的陶瓷基复合材料涡轮导向叶片进行效果验证，具体为：按照《GJB 150.16A-2009军用装备实验室环境试验方法第16部分：振动试验》进行验证，验证结果为：在10-2000Hz频带、总均方根加速度25grms条件下，试验后叶片结构完整，未出现开裂、分层、掉块等异常现象，说明本发明方法可提升构件结构的可靠性。The effect of the ceramic matrix composite turbine guide vanes prepared in Examples 1-3 is verified, specifically: according to "GJB 150.16A-2009 Laboratory Environmental Test Methods for Military Equipment Part 16: Vibration Test", the verification results are: Under the conditions of 10-2000Hz frequency band and total root mean square acceleration of 25grms, the blade structure is complete after the test, and there is no abnormal phenomenon such as cracking, delamination, and block drop, indicating that the method of the present invention can improve the reliability of the component structure.
以上所述仅为本发明的较佳实施例，并不用以限制本发明，凡在本发明的精神和原则之内，所作的任何修改、等同替换、改进等，均应包含在本发明的保护范围之内。The above descriptions are only preferred embodiments of the present invention, and are not intended to limit the present invention. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included in the protection of the present invention. within the range.
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