CN114057491A - 一种陶瓷基复合材料脉冲爆震发动机燃烧室的制备方法 - Google Patents
一种陶瓷基复合材料脉冲爆震发动机燃烧室的制备方法 Download PDFInfo
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Abstract
本发明公开了一种陶瓷基复合材料脉冲爆震发动机燃烧室的制备方法,包括以下步骤:分别制备燃烧室壳体和螺旋体的纤维预制体,然后在纤维预制体表面制备界面层和碳化硅陶瓷基体层,加工至设计尺寸,得到陶瓷基复合材料燃烧室壳体和螺旋体;将螺旋体按照设计要求插入燃烧室壳体内,在其接触部位制备通孔,然后将销钉插入通孔内进行同质连接,再加工至设计尺寸,损伤修复后,即制得陶瓷基复合材料脉冲爆震发动机燃烧室。本发明制得的陶瓷基复合材料脉冲爆震发动机燃烧室耐温性得到大幅提升,同时可显著降低其重量。
Description
技术领域
本发明涉及爆震发动机制备技术领域,具体涉及一种陶瓷基复合材料脉冲爆震发动机燃烧室的制备方法。
背景技术
脉冲爆震循环具有循环效率高、燃烧过程自增压等特性,被认为是一种最有可能替代传统涡轮发动机中等压循环而成为下一代发动机的热力循环方式。脉冲爆震发动机就是一种采用脉冲爆震循环的新型动力装置,它利用脉冲爆震燃烧室来替代传统涡轮发动机中的等压燃烧室(包括主燃烧室和加力燃烧室),从而将传统涡轮发动机中的等压循环转化为脉冲爆震循环,能大大提高传统涡轮发动机的性能水平。
为了能够增强脉冲爆震燃烧室内部燃烧场的湍流度,有效促进火焰加速,从而缩短脉冲爆震发动机的长度,在燃烧室内设置Shchelkin螺旋,能够有效增强流场的湍流度,从而促进火焰加速,使火焰锋面尽快与前导激波耦合,从而形成爆震波。目前,具有Shchelkin螺旋结构的脉冲爆震燃烧室基本采用镍基和钴基高温合金作为其主体材料,其耐温性一般不超过1050℃,难以满足燃烧室工作温度更高、结构重量更轻的需求。陶瓷基复合材料作为一种具有低密度、耐高温、抗氧化、耐腐蚀、高韧性等各种材料优点的热结构功能一体化材料,被国际公认为是发展先进发动机高温部件最具潜力的材料之一,有望大幅提升脉冲爆震燃烧室的综合性能,然而,由于具有Shchelkin螺旋结构的脉冲爆震燃烧室内部具有复杂的螺旋结构,采用陶瓷基复合材料进行制备时,难以将燃烧室的筒形外壁和螺旋结构直接成型。
发明内容
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脉冲爆震发动机的制备方法,以解决现有技术中用陶瓷基复合材料制备脉冲爆震发动机时,难以将燃烧室壳体和螺旋体直接成型的问题。
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脉冲爆震发动机燃烧室的制备方法,包括以下步骤:
(1)分别制备均夹持有模具的燃烧室壳体纤维预制体和螺旋体纤维预制体;其中模具具有导气孔;
(2)利用化学气相沉积法在燃烧室壳体纤维预制体和螺旋体纤维预制体表面制备界面层;
(3)利用化学气相沉积法在界面层表面制备碳化硅陶瓷基体,然后将模具去除,再机械加工至设计尺寸,得到陶瓷基复合材料燃烧室壳体和螺旋体;
(4)将螺旋体按照设计要求插入燃烧室壳体内,在其接触部位制备通孔,然后将碳化硅陶瓷基复合材料销钉插入通孔内,再利用碳化硅,通过化学气相沉积法完成销钉、燃烧室壳体和螺旋体的同质连接,再机械加工至设计尺寸,最后再利用碳化硅,通过化学气相沉积法进行损伤修复,即制得陶瓷基复合材料脉冲爆震发动机燃烧室。
本发明的有益效果为:对于陶瓷基复合材料的连接技术,采用金属件连接时,有使用温度受制于连接件耐温性、金属与陶瓷复合材料热物理性能差异引起的应力和变形等问题;采用高温胶粘接时,有连接强度低、高温胶长时使用有脱粘等风险。本发明创新性地采用了燃烧室筒体和螺旋体分别制备,并通过同质材料一体化装配的技术途径(同质连接),不仅能够有效保证其内外型面和螺旋体的尺寸精度,还能够保证整体构件的耐温性不受连接件影响,有效避免了上述问题。
在上述技术方案的基础上,本发明还可以做如下改进:
进一步,步骤(1)中均夹持有模具的燃烧室壳体纤维预制体和螺旋体纤维预制体通过以下步骤制得:
(1.1)以燃烧室壳体的筒体内圆为基准,沿筒体轴向拉伸,将设计模型中的螺旋体结构切分为单独的实体模型,即得到燃烧室壳体和螺旋体的三维模型;
(1.2)分别按照燃烧室壳体和螺旋体三维模型的结构与形状尺寸,以耐高温材料为原材料,分别制备燃烧室壳体模具和螺旋体的模具;
(1.3)以碳纤维和/或碳化硅纤维为原料,分别按照燃烧室壳体模具和螺旋体模具的尺寸进行预制体的定型,得到均夹持有模具的燃烧室壳体纤维预制体和螺旋体纤维预制体;
进一步,步骤(1.2)中耐高温材料为电极石墨或高纯石墨。
进一步,高纯石墨是指石墨的含碳量>99.99%。
进一步,步骤(1.3)中燃烧室壳体纤维预制体通过将原材料制制成二维平纹编织布,然后缠绕在燃烧室壳体模具的内模上,随后合并燃烧室壳体模具的外模完成定型。
进一步,步骤(1.3)中螺旋体纤维预制体通过将原材料采用三维多向编织、2.5维编织或三维针刺,先进行螺旋体条状预制体的成型,然后将其卡入螺旋体模具的螺旋凹槽内完成定型。
采用上述进一步技术方案的有益效果为:采用上述编织方法,有利于预制体成型,同时能够保证其尺寸和型面的精度以及结构的强度。
进一步,步骤(2)中界面层为热解碳或氮化硼。
进一步,步骤(2)中界面层厚度为100-600nm。
进一步,步骤(2)中化学气相沉积法的沉积次数为1-3次。
进一步,界面层为热解碳时,化学气相沉积法的沉积压力为50-1000Pa,沉积温度为900-1100℃,沉积时间为20-60h,沉积气体为丙烯和氢气的混合气体,沉积完成后,再在真空条件下,于2000-2220℃热处理20-30h;其中,丙烯和氢气的流量比为1:1-5。
进一步,界面层为氮化硼时,化学气相沉积法的沉积压力为50-1000Pa,沉积温度为650-1000℃,沉积时间为15-35h,沉积气体为氩气、氢气、氨气和三氯化硼的混合气体;其中,氩气、氢气、氨气和三氯化硼的流量比为1:1-3:2-8:2-8。
采用上述进一步技术方案的有益效果为:上述界面层有助于陶瓷基复合材料具有优良的韧性和强度。
进一步,步骤(3)中化学气相沉积法的沉积次数为4-8次,步骤(4)中化学气相沉积法的沉积次数为1-3次。
进一步,步骤(3)中化学气相沉积法和步骤(4)中化学气相沉积法的工艺参数相同。
进一步,化学气相沉积法的工艺参数为:沉积压力为200-5000Pa,沉积温度900-1200℃,沉积时间为30-80h,沉积气体为三氯甲基硅烷、氢气和氩气的混合气体。
进一步,三氯甲基硅烷∶氢气∶氩气的流量比为1:5-15:10-20。
进一步,步骤(4)中通孔孔径为2-8mm。
进一步,步骤(4)中销钉与通孔为过盈配合,过盈量为0.01-0.08mm。
本发明还提供上述制备方法制得的陶瓷基复合材料脉冲爆震发动机燃烧室。
本发明具有以下有益效果:
一、由于陶瓷基复合材料的密度为2.0-2.5g/cm3,传统高温合金材料的密度约为8.5-8.9g/cm3,因此本发明采用陶瓷基复合材料作为脉冲爆震燃烧室构件的主体材料,可降低构件结构重量50%以上;此外,陶瓷基复合材料在无冷却措施的条件下,可在1350℃以下长时间(>100h)、在1650℃以下短时间(<10h)保持85%以上的力学性能,相比高温合金材料1050℃的耐温能力,可大幅提升燃烧室构件的耐温能力。
二、燃烧室壳体、螺旋体和连接件均为力学、物理性能完全一致的同质陶瓷基复合材料,因此燃烧室构件的各组成部分具有良好的物理化学相容性。此外,采用燃烧室壳体和螺旋体结构分别制备的技术手段,可以通过分别成型手段,实现复杂螺旋结构的加工,构件精度可满足GB/T 1804-2000所规定的m级尺寸精度和GB/T 1184-1996所规定的K级形位精度等级要求。本发明所提出的采用燃烧室壳体和螺旋体结构分别制备,并通过同质材料一体化装配的技术途径,可以实现具有复杂螺旋结构的陶瓷基复合材料脉冲爆震燃烧室构件制备,不仅能够有效保证其内外型面和螺旋体的尺寸精度,还能够保证整体构件的耐温性不受连接件影响。
附图说明
图1为夹持有模具的燃烧室壳体纤维预制体示意图(外模部分扇形段未示);
图2为螺旋体模具示意图;
图3为螺旋体条状预制体示意图;
图4为夹持有模具的螺旋体纤维预制体示意图;
图5为燃烧室壳体示意图;
图6为燃烧室壳体、螺旋体和销钉连接后的示意图;
图7为陶瓷基复合材料脉冲爆震发动机燃烧室成品示意图。
其中,1、内模;2、外模扇形段;3、法兰;4、连接件;5、燃烧室壳体纤维预制体;6、螺旋体模具;7、螺旋体条状预制体;8、螺旋体纤维预制体;9、销钉;10、螺旋体;11、燃烧室壳体。
具体实施方式
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。
实施例1:
一种陶瓷基复合材料脉冲爆震发动机燃烧室,其制备方法包括以下步骤:
(1)工艺拆分
以燃烧室壳体的筒体内圆为基准,沿筒体轴向拉伸,将设计模型中的螺旋体结构切分为单独的实体模型,即得到燃烧室壳体11和螺旋体10的三维模型;
(2)模具制备
以高纯石墨为原材料,分别按照燃烧室壳体11和螺旋体10三维模型的结构与形状尺寸设计和制备模具,燃烧室壳体模具包括内膜1、外模、法兰3和连接件4,外模由两个具有连接孔的外模扇形段2构成,螺旋体模具6为具有螺旋凹槽的筒形结构,螺旋凹槽型面与螺旋体10一致;其中,燃烧室壳体模具和螺旋体模具6均具有导气孔;
(3)纤维预制体的定型
按照燃烧室壳体模具的尺寸,将碳纤维制成二维平纹编织布,然后缠绕在燃烧室壳体模具的内膜1上,随后合并燃烧室壳体模具的外模完成定型,得到夹持有模具的燃烧室壳体纤维预制体5;以碳纤维为原料,按照螺旋体模具6的尺寸,采用三维多向编织的方法进行螺旋体条状预制体7的成型,并将其卡入螺旋体模具6的螺旋凹槽内完成定型,得到夹持有模具的螺旋体纤维预制体8;
(4)界面层的制备
将均夹持有模具的燃烧室壳体纤维预制体5和螺旋体纤维预制体8放置在化学气相沉积炉内,炉体内压力为350Pa,升温至950℃,保温2h后,通入丙烯和氢气的混合气体,丙烯和氢气的流量比为1:2,沉积50h后,降温至室温,按照上述操作循环执行2次后,在真空条件下,于2000℃热处理30h,然后降温至室温,即在燃烧室壳体纤维预制体5和螺旋体纤维预制体8表面均制备了热解碳界面层;其中,界面层厚度均为200nm;
(5)陶瓷基体的制备
将制备了热解碳界面层的均夹持有模具的燃烧室壳体纤维预制体5和螺旋体纤维预制体8放置于碳化硅化学气相沉积炉内,炉体内压力为400Pa,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1:10:15,沉积60h后,继续保温2h,降温至室温;此步骤循环执行8次,然后将模具去除,再机械加工至设计尺寸,得到陶瓷基复合材料燃烧室壳体11和螺旋体10;
(6)同质连接及加工
将螺旋体10按照设计要求插入燃烧室壳体11内,采用机械加工的方式,在其接触部位制备孔径为4mm的通孔,然后将碳化硅陶瓷基复合材料销钉9插入通孔内,销钉9与通孔为过盈配合,过盈量为0.05mm,将制得的装配体置于碳化硅化学气相沉积炉内,完成销钉9、燃烧室壳体11和螺旋体10的同质连接,此同质连接循环执行2次,再机械加工至设计尺寸,最后再置于碳化硅化学气相沉积炉内,进行损伤修复,此修复循环执行2次,即制得陶瓷基复合材料脉冲爆震发动机燃烧室;其中,化学气相沉积的工艺参数与步骤(5)中一致。
实施例2:
一种陶瓷基复合材料脉冲爆震发动机燃烧室,其制备方法包括以下步骤:
(1)工艺拆分
以燃烧室壳体11的筒体内圆为基准,沿筒体轴向拉伸,将设计模型中的螺旋体10结构切分为单独的实体模型,即得到燃烧室壳体11和螺旋体10的三维模型;
(2)模具制备
以高纯石墨为原材料,分别按照燃烧室壳体11和螺旋体10三维模型的结构与形状尺寸设计和制备模具,燃烧室壳体模具包括内膜1、外模、法兰3和连接件4,外模由两个具有连接孔的外模扇形段2构成,螺旋体模具6为具有螺旋凹槽的筒形结构,螺旋凹槽型面与螺旋体10一致;其中,烧室壳体模具和螺旋体模具6均具有导气孔;
(3)纤维预制体的定型
按照燃烧室壳体模具的尺寸,将碳纤维制成二维平纹编织布,然后缠绕在燃烧室壳体模具的内膜1上,随后合并燃烧室壳体模具的外模完成定型,得到夹持有模具的燃烧室壳体纤维预制体5;以碳纤维为原料,按照螺旋体模具6的尺寸,采用2.5维编织的方法进行螺旋体条状预制体7的成型,并将其卡入螺旋体模具6的螺旋凹槽内完成定型,得到夹持有模具的螺旋体纤维预制体8;
(4)界面层的制备
将均夹持有模具的燃烧室壳体纤维预制体5和螺旋体纤维预制体8放置在化学气相沉积炉内,炉体内压力为350Pa,升温至950℃,保温2h后,通入氩气、氢气、氨气和三氯化硼的混合气体,氩气、氢气、氨气和三氯化硼的流量比为1:2:3:3,沉积25h后,降温至室温,按照上述操作循环执行2次后,然后降温至室温,即在燃烧室壳体纤维预制体5和螺旋体纤维预制体8表面制备了氮化硼界面层;其中,界面层厚度均为300nm;
(5)陶瓷基体的制备
将制备了氮化硼界面层的均夹持有模具的燃烧室壳体纤维预制体5和螺旋体纤维预制体8放置于碳化硅化学气相沉积炉内,炉体内压力为200Pa,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1h,降温至室温,此步骤循环执行4次,然后将模具去除,再机械加工至设计尺寸,得到陶瓷基复合材料燃烧室壳体11和螺旋体10;
(6)同质连接及加工
将螺旋体10按照设计要求插入燃烧室壳体11内,采用机械加工的方式,在其接触部位制备孔径为2mm的通孔,然后将碳化硅陶瓷基复合材料销钉9插入通孔内,销钉9与通孔为过盈配合,过盈量为0.01mm,将制得的装配体置于碳化硅化学气相沉积炉内,完成销钉9、燃烧室壳体11和螺旋体10的同质连接,再机械加工至设计尺寸,最后再置于碳化硅化学气相沉积炉内,进行损伤修复,即制得陶瓷基复合材料脉冲爆震发动机燃烧室;其中,化学气相沉积的工艺参数与步骤(5)中一致。
实施例3:
一种陶瓷基复合材料脉冲爆震发动机燃烧室,其制备方法包括以下步骤:
(1)工艺拆分
以燃烧室壳体11的筒体内圆为基准,沿筒体轴向拉伸,将设计模型中的螺旋结构切分为单独的实体模型,即得到燃烧室壳体11和螺旋体10的三维模型;
(2)模具制备
以高纯石墨为原材料,分别按照燃烧室壳体11和螺旋体10三维模型的结构与形状尺寸设计和制备模具,燃烧室壳体模具包括内膜1、外模、法兰3和连接件4,外模由两个具有连接孔的外模扇形段2构成,螺旋体模具6为具有螺旋凹槽的筒形结构,螺旋凹槽型面与螺旋体10一致;其中,燃烧室壳体模具和螺旋体模具6均具有导气孔;
(3)纤维预制体的定型
按照燃烧室壳体模具的尺寸,将碳纤维制成二维平纹编织布,然后缠绕在燃烧室壳体模具的内膜1上,随后合并燃烧室壳体模具的外模完成定型,得到夹持有模具的燃烧室壳体纤维预制体5;以碳纤维为原料,按照螺旋体模具6的尺寸,采用三维针刺的方法进行螺旋体条状预制体7的成型,并将其卡入螺旋体模具6的螺旋凹槽内完成定型,得到夹持有模具的螺旋体纤维预制体8;
(4)界面层的制备
将均夹持有模具的燃烧室壳体纤维预制体5和螺旋体纤维预制体8放置在化学气相沉积炉内,炉体内压力为1000Pa,升温至1100℃,保温1h后,通入丙烯和氢气的混合气体,丙烯和氢气的流量比为1:5,沉积20h后,降温至室温,按照上述操作循环执行3次后,在真空条件下,于2200℃热处理20h,然后降温至室温,即在燃烧室壳体纤维预制体5和螺旋体纤维预制体8表面制备热解碳界面层;其中,界面层厚度均为600nm;
(5)陶瓷基体的制备
将制备了热解碳界面层的均夹持有模具的燃烧室壳体纤维预制体5和螺旋体纤维预制体8放置于碳化硅化学气相沉积炉内,炉体内压力为5000Pa,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6次,然后将模具去除,再机械加工至设计尺寸,得到陶瓷基复合材料燃烧室壳体11和螺旋体10;
(6)同质连接及加工
将螺旋体10按照设计要求插入燃烧室壳体11内,采用机械加工的方式,在其接触部位制备孔径为8mm的通孔,然后将碳化硅陶瓷基复合材料销钉9插入通孔内,销钉9与通孔为过盈配合,过盈量为0.08mm,将制得的装配体置于碳化硅化学气相沉积炉内,完成销钉9、燃烧室壳体11和螺旋体10的同质连接,此同质连接循环执行3次,再机械加工至设计尺寸,最后再置于碳化硅化学气相沉积炉内,进行损伤修复,此修复循环执行3次,即制得陶瓷基复合材料脉冲爆震发动机燃烧室;其中,化学气相沉积的工艺参数与步骤(5)中一致。
效果验证
一、对实施例1-3制备的陶瓷基复合材料脉冲爆震发动机燃烧室进行性能检测,密度测试方法为:GB/T 2997-2000精细陶瓷密度和显气孔率试验方法;拉伸强度测试方法为:GJB 6475-2008连续纤维增强陶瓷基复合材料常温拉伸性能试验方法;检测结果见表1,由表1可知,本发明制备的陶瓷基复合材料脉冲爆震发动机燃烧室性能参数较优,其耐温性提高了300-600℃,结构减重可达50%以上,常用镍基高温合金的密度为8.5-8.9g/cm3,耐温性不超过1050℃,1050℃时的高温强度不超过150MPa,熔点为1260℃(即在此温度下丧失全部强度)。
表1陶瓷基复合材料脉冲爆震发动机燃烧室的密度、拉伸强度和耐温性
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。
Claims (10)
1.一种陶瓷基复合材料脉冲爆震发动机燃烧室的制备方法,其特征在于,包括以下步骤:
(1)分别制备均夹持有模具的燃烧室壳体纤维预制体(5)和螺旋体纤维预制体(8);其中模具具有导气孔;
(2)利用化学气相沉积法在燃烧室壳体纤维预制体(5)和螺旋体纤维预制体(8)表面制备界面层;
(3)利用化学气相沉积法在界面层表面制备碳化硅陶瓷基体,然后将模具去除,再机械加工至设计尺寸,得到陶瓷基复合材料燃烧室壳体(11)和螺旋体(10);
(4)将螺旋体(10)按照设计要求插入燃烧室壳体(11)内,在其接触部位制备通孔,然后将碳化硅陶瓷基复合材料销钉(9)插入通孔内,再利用碳化硅,通过化学气相沉积法完成销钉(9)、燃烧室壳体(11)和螺旋体(10)的同质连接,再机械加工至设计尺寸,最后再利用碳化硅,通过化学气相沉积法进行损伤修复,即制得陶瓷基复合材料脉冲爆震发动机燃烧室。
2.根据权利要求1所述的陶瓷基复合材料脉冲爆震发动机燃烧室的制备方法,其特征在于,步骤(1)中均夹持有模具的燃烧室壳体纤维预制体(5)和螺旋体纤维预制体(8)通过以下步骤制得:
(1.1)以燃烧室壳体的筒体内圆为基准,沿筒体轴向拉伸,将设计模型中的螺旋体结构切分为单独的实体模型,即得到燃烧室壳体(11)和螺旋体(10)的三维模型;
(1.2)分别按照燃烧室壳体(11)和螺旋体(10)三维模型的结构与形状尺寸,以耐高温材料为原材料,分别制备燃烧室壳体模具和螺旋体模具(6);
(1.3)以碳纤维和/或碳化硅纤维为原材料,分别按照燃烧室壳体模具和螺旋体模具(6)的尺寸,进行燃烧室壳体纤维预制体(5)和螺旋体纤维预制体(8)的定型,得到均夹持有模具的燃烧室壳体纤维预制体(5)和螺旋体纤维预制体(8)。
3.根据权利要求2所述的陶瓷基复合材料脉冲爆震发动机燃烧室的制备方法,其特征在于,步骤(1.3)中燃烧室壳体纤维预制体(5)通过将原材料制成二维平纹编织布,然后缠绕在燃烧室壳体模具的内膜(1)上,随后合并燃烧室壳体模具的外模完成定型。
4.根据权利要求2所述的陶瓷基复合材料脉冲爆震发动机燃烧室的制备方法,其特征在于,步骤(1.3)中螺旋体纤维预制体(8)通过将原材料采用三维多向编织、2.5维编织或三维针刺,先进行螺旋体条状预制体(7)的成型,然后将其卡入螺旋体模具(6)的螺旋凹槽内完成定型。
5.根据权利要求1所述的陶瓷基复合材料脉冲爆震发动机燃烧室的制备方法,其特征在于,步骤(2)中界面层为热解碳或氮化硼。
6.根据权利要求1所述的陶瓷基复合材料脉冲爆震发动机燃烧室的制备方法,其特征在于,步骤(2)中界面层厚度为100-600nm。
7.根据权利要求1所述的陶瓷基复合材料脉冲爆震发动机燃烧室的制备方法,其特征在于,步骤(3)中化学气相沉积法的沉积次数为4-8次,步骤(4)中化学气相沉积法的沉积次数为1-3次。
8.根据权利要求1所述的陶瓷基复合材料脉冲爆震发动机燃烧室的制备方法,其特征在于,步骤(4)中通孔孔径为2-8mm。
9.根据权利要求1所述的陶瓷基复合材料脉冲爆震发动机燃烧室的制备方法,其特征在于,步骤(4)中销钉(9)与通孔为过盈配合,过盈量为0.01-0.08mm。
10.权利要求1-9任一项所述的陶瓷基复合材料脉冲爆震发动机燃烧室的制备方法制得的陶瓷基复合材料脉冲爆震发动机燃烧室。
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