GAS TURBINE FUEL NOZZLE LEAK DETECTION PRESSURE TEST TOOL AND METHOD FOR LEAK DETECTION

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.

主权项

1. A leak detection pressure test tool for a gas turbine engine nozzle of the type having a rocket swirler with a mounting neck, a plurality of swirler air foils radially projecting outwardly from the neck, having cambered upper and lower surfaces, at least one of the airfoil surfaces defining an airfoil orifice that is circumscribed radially and axially by a generally annular can, the rocket swirler having isolated fuel distribution passages in communication with the mounting neck and the airfoil orifice, the tool comprising:
a mounting flange adapted for abutment proximal a rocket swirler mounting neck and annular can; and at least one airfoil orifice clamp coupled to and projecting from the mounting flange, the clamp having a pair of cooperative biased jaws that are adapted for capture of an airfoil there between and for sealing an airfoil orifice with a surface defined by one of the jaws when the jaws are inserted into a rocket swirler annular can by abutment of the mounting flange proximal the swirler mounting neck.