Fabrication of High Pressure Rocket Combustor by Powder Metallurgy

粉末冶金高压火箭燃烧室的制造

基本信息

批准号：
01850151
负责人：
WATANABE Ryuzo
金额：
$ 3.97万
依托单位：
Tohoku University
依托单位国家：
日本
项目类别：
Grant-in-Aid for Developmental Scientific Research
财政年份：
1989
资助国家：
日本
起止时间：
1989 至 1991
项目状态：
已结题

来源：
https://kaken.nii.ac.jp/en/grant/KAKENHI-PROJECT-01850151/
关键词：
Rocket combustor Space shuttle Sintered outer shell Long-life rocket engine Powder Metallurgy Sintering bonding Bonding strength Yound's modulus 軽量合金傾斜機能化レ-ザスペックル法

项目摘要

The processing conditions for the fabrication of high pressure and long life rocket thrust chamber with sintered outer shell were investigated. Powder metallurgical route was selectively employed because of its viability of property control and shape forming. The microstructural control and mechanical property measurements were studied on the alloy systems of of Al-Cu and Cu-Ag for the application to the outer shell of the thrust chamber. The bonding strength of the sintered interface between the outer shell and copper inner shell, as well as net shaping of throat model which simulates the actual rocket thrust chamber. Perticular attention was paid on the control of the porosity of sintered outer shell, which is effective for the lower stiffness of the sintered shell and thus ensures long life use of the rocket engine.The plating of tin or siler was found to be effective for an improved bonding between sintered outer shell and the copper inner throat. A sufficient bonding strength, as well as deffect-free bonding interface, was realized by the control of liquid phase formation and pressurizing during sinter-bonding. The bonding behavior between the outer and inner shell was studied more in datail using a more realistic throat model. Insufficient bonding was often observed at the throat. the shoulder and the edge of the straight part of the model ; which were eliminated by proper conditions of the pressurizing and liquid phase formation.

研究了用烧结的外壳制造高压和长寿命火箭推室的加工条件。由于其性质控制和形状形成的可行性，粉末冶金路线被选择性地采用。在Al-Cu和Cu-Ag的合金系统上研究了微观结构控制和机械性能测量，以应用于推力室的外壳。外壳和铜内壳之间烧结的界面的粘结强度，以及模拟实际火箭推室的喉咙模型的净成型。在控制烧结外壳的孔隙率上引起了巨大的注意改善了烧结的外壳和铜内喉咙之间的键合。通过控制液相形成和烧结期间的加压来实现足够的键合强度以及无脱离键的界面。使用更逼真的喉咙模型，在Datail中对外壳和内壳之间的键合行为进行了更多研究。在喉咙上经常观察到粘结不足。模型的肩膀和边缘；由加压和液相形成的适当条件消除了。