DEVELOPMENT STUDY ON TURBINE DISK MADE OF C/C COMPOSITE SUBJECTED TO HIGH TEMPERATURE ENVIRONMENT

高温环境下C/C复合材料涡轮盘的研制研究

• 批准号: 11305047
• 负责人: HATTA Hiroshi
• 金额: $ 25.22万
• 依托单位: INSTITUTE OF SPACE AND ASTRONAUTICAL SCIENCE
• 依托单位国家: 日本
• 项目类别: Grant-in-Aid for Scientific Research (A)
• 财政年份: 1999
• 资助国家: 日本
• 起止时间: 1999 至 2002
• 项目状态: 已结题
• 来源: https://kaken.nii.ac.jp/grant/KAKENHI-PROJECT-11305047/
• 关键词: Carbon fiber reinforced carbon matrix composites; Turbine disk; Spin burst test; Fly-out; Tensile strength; Fatigue strength; Notch sensitivity; 炭素繊維強化炭素; C; C複合材料; 回転試験; 回転破壊

A feasibility study of three-dimensionally fiber-reinforced carbon-carbon composites (3D-C/Cs) for application to a turbine disk of ATREX (Air-turbo-ramjet engine with expander cycle) was carried out. Spin burst tests at room temperature were conducted using 3D-C/C disks, and the fracture behaviors were characterized. A 3D-C/C disk was totally fractured at a peripheral speed of 516 m/s (r = 150 mm), which is sufficient for the ATREX application. However fiber-bundles at the disk periphery prematurely suffered micro-scale damage, and fragments of the fiber bundle unit flew out before total fracture occurred. In order to prevent the fly-out behavior, the disk was impregnated with Si only near its periphery. Although This treatment increased the initiation speed of the fly-out behavior, this improvement was considered insufficient for purposes of the ATREX application. Next, a simplified analysis was conducted to characterize the fly-out behavior. Based on this analysis, the following three measures were discussed: (1)decreasing bundle thickness, (i.e.,using fine fiber texture),(2)increasing toughness of the fiber bundle interface, and (3)minimizing local curvature in waviness of the fiber bundles in the circumferential direction. The third countermeasure was found to be most effective and disks minimizing local curvature were verified to satisfy ATREX requirement.In addition to above study, experiments to confirm durability of 3D-C/Cs were carried out. This category of study included, high temperature behavior, creep, fatigue, and notch insensitivity. The 3D-C/Cs were found to possess sufficient above durability for the ATREX application.

对三维纤维增强碳/碳复合材料（3D-C/Cs）应用于ATREX（膨胀循环空气涡轮冲压发动机）涡轮机盘的可行性进行了研究。采用3D-C/C盘进行了室温下的旋转爆破试验，并对其断裂行为进行了表征。3D-C/C盘在516 m/s（r = 150 mm）的圆周速度下完全断裂，这对于ATREX应用是足够的。然而，在磁盘周边的纤维束过早地遭受微尺度的损伤，和纤维束单元的碎片飞出之前，总断裂发生。为了防止飞出行为，盘仅在其周边附近浸渍有Si。尽管这种处理增加了飞出行为的起始速度，但这种改善被认为不足以用于ATREX应用的目的。接下来，进行简化分析以表征飞出行为。在此基础上，讨论了以下三种措施：（1）减小管束厚度，使用细纤维结构），（2）增加纤维束界面的韧性，和（3）使纤维束在圆周方向上的波纹度的局部曲率最小化。第三种对策是最有效的，并且最小化局部曲率的盘被验证为满足ATREX要求。除了上述研究之外，还进行了实验以确认3D-C/Cs的耐久性。这类研究包括高温行为、蠕变、疲劳和缺口不敏感性。发现3D-C/C对于ATREX应用具有足够的上述耐久性。

项目成果

K.Goto, H.Hatta, M.Oe, T.Koizumi: "Tensile strength and deformation of a 2D Carbon-Carbon composite at elevated temperatures"J.Am.Ceram.Soc.. (in printing).

K.Goto、H.Hatta、M.Oe、T.Koizumi：“高温下二维碳-碳复合材料的拉伸强度和变形”J.Am.Ceram.Soc.（印刷中）。

Hiroshi Hatta, Ken Goto, T.Sato, N.Tanatsugu: "Applications of Carbon-Carbon Composites to an Engine for a Future Space Vehicle"ACM. 12(2-3). 237-259 (2003)

Hiroshi Hatta、Ken Goto、T.Sato、N.Tanatsugu：“碳-碳复合材料在未来航天器发动机中的应用”ACM。

H.Hatta, K.Goto, T.Sato, N.Tanatsugu: "Applications of Carbon-Carbon Composites to an Engine for a Future Space Plane"Advanced Composite Matrials. (in printing).

H.Hatta、K.Goto、T.Sato、N.Tanatsugu：“碳-碳复合材料在未来太空飞机发动机中的应用”先进复合材料。

Ken Goto, Hiroshi Hatta, Yasuo Kogo, Hiroshi Fukuda, Tetsuya Sato, Nobuhiro Tanatsugu: "Carbon-Carbon Composite Turbine Disk for the Air Turbo-Ram-Jet Engine (ATREX)"ACM. 12(2-3). 205-222 (2003)

Ken Goto、Hiroshi Hatta、Yasuo Kogo、Hiroshi Fukuda、Tetsuya Sato、Nobuhiro Tanatsugu：“用于空气涡轮冲压喷气发动机（ATREX）的碳-碳复合材料涡轮盘”ACM。

Y.Kogo, H.Hatta, M.Toyoda, T.Sugibayashi: "Application of three-dimensionally reinforced carbon/carbon composites to dovetail joint structures"Compos.Sci.Tech.. 62(16). 2143-2152 (2002)

Y.Kogo、H.Hatta、M.Toyoda、T.Sugibayashi：“三维增强碳/碳复合材料在燕尾接头结构中的应用”Compos.Sci.Tech.. 62(16)。