| 摘要 |
<p>The invention relates to an injector for unstable liquids to be used as rocket engine fuels and to a process for manufacturing the same. According to the invention, the injector comprises a body () wherein a support () is mounted and axially provided with a circular orifice (), inside the support () there being a valve () which can slide between an upstream end position in which the valve () is in contact with a valve seat () confining an intake orifice () which is thereby tightly closed and a downstream end position in which the valve () tightly closes another orifice (), an annular groove which can be cut into the body () possibly accommodating an annular mini magnet (). The process, as claimed by the invention, consists in cutting a blind annular axial orifice () into a primary metal bar (), whereinto a hexagonal mandrel () is introduced and applying a quasi-uniform pressure onto an outer surface of the bar (), the value of the said pressure being higher than the value of the flowing pressure of the metal of which the bar () is made, the pressure being applied by normal squeezing between some squeezing jaws () up to the complete deformation of the material around the blind annular orifice () which gets the shape of the mandrel (), after which the bar () is released from the jaws () and the mandrel () is withdrawn, then the bar () is machined externally and internally by lathe turning in order to cut out the support () therefrom.</p> |
