SYSTEMS FOR CREATING A SEAL ABOUT A LIQUID FUEL INJECTOR IN A GAS TURBINE ENGINE

A fuel nozzle assembly for a gas turbine engine is disclosed herein. The fuel nozzle assembly may include a fuel injector (204) including an outer jacket (206) having a first end (208) and a second end (210) with a threaded surface (212) disposed therebetween. The first end (208) of the fuel injecto...

Full description

Saved in:
Bibliographic Details
Main Authors JOHNSON, Thomas Edward, GRAHAM, Kaitlin Marie
Format Patent
LanguageEnglish
French
German
Published 02.01.2019
Subjects
BLASTING
BURNERS
COMBUSTION APPARATUS
COMBUSTION PROCESSES
GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGHVELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
HEATING
LIGHTING
MECHANICAL ENGINEERING
WEAPONS
Online AccessGet full text

Cover

More Information
Summary:A fuel nozzle assembly for a gas turbine engine is disclosed herein. The fuel nozzle assembly may include a fuel injector (204) including an outer jacket (206) having a first end (208) and a second end (210) with a threaded surface (212) disposed therebetween. The first end (208) of the fuel injector (204) may include a cylindrical sealing surface (240). The fuel nozzle assembly also may include an annular hub (130) including an aperture (230) having a first end (232) and a second end (2234) with a threaded surface (236) disposed therebetween. The aperture (230) may be configured to at least partially house the fuel injector (204) therein and includes a conical seat (244) about the first end (232). The cylindrical sealing surface (240) may swage inward along the conical seat (244) to form a seal therebetween as the liquid fuel injector (240) is threaded into the aperture (230).
Bibliography:Application Number: EP20160161511