公开(公告)号：US20150052980A1

公开(公告)日：2015-02-26

申请号：US13972203

申请日：2013-08-21

申请人： Danny M. Sheldon ,  Kristine A. Kushner ,  Trent Lewis ,  Dane J. Hurt

发明人： Danny M. Sheldon ,  Kristine A. Kushner ,  Trent Lewis ,  Dane J. Hurt

IPC分类号： G01M3/04

CPC分类号： G01M3/025 ,  G01M3/3209 ,  G01M3/3272

摘要： Internally shielded fuel passage orifices in nozzle rocket swirler airfoils are sealed with the pressure test tool. Pinch clamps on the test tool are introduced into the fuel nozzle rocket swirler. The clamps are tightened over the airfoil orifices to plug or otherwise seal them and their fuel passages within the nozzle assembly. The nozzle assembly fuel passages are subsequently pressurized. Pressure is monitored to determine whether the nozzle is properly sealed (i.e., no pressure decay) or whether it has a leak-causing structural defect. Pressure drop in the tested component during the test cycle is indicative of a leak, in the nozzle's fuel passages, caused for example by a structural defect in the component. The test system may also be utilized in conjunction with individual rocket swirlers that are not incorporated within a complete fuel nozzle assembly.

摘要翻译： 喷嘴火箭旋流器翼型中的内部屏蔽燃料通道孔口用压力测试工具密封。 测试工具上的夹紧夹具被引入燃料喷嘴火箭旋流器。 夹紧件紧固在翼型孔上，以将其和喷嘴组件内的燃料通道塞住或以其他方式密封。 喷嘴组件燃料通道随后被加压。 监测压力以确定喷嘴是否被适当地密封（即，没有压力衰减）或者其是否具有导致泄漏的结构缺陷。 在测试循环期间测试组件中的压降表示在喷嘴的燃料通道中由例如组件中的结构缺陷引起的泄漏。 测试系统还可以与不并入整个燃料喷嘴组件中的单个火箭旋流器结合使用。