Patent ID: 9546600
Date: 2017-01-17
CPC Classifications: F02C,F23K,F23R

Claim:
1. A nozzle for a gas turbine engine, comprising: a base portion including a first axial end of the nozzle; an outlet portion including a second axial end of the nozzle, wherein the second axial end is the axially opposite end of the nozzle relative to the first axial end; a connection section extending from the base portion to the outlet portion, wherein the connection section couples the base portion to the outlet portion; a first passage having a first inlet at the first axial end and a first passage outlet at the second axial end; and a second passage radially outward of the first passage, wherein the second passage is a fuel passage, the second passage having a second inlet at the first axial end, a second outlet at the second axial end, an aperture located in the base portion radially outward of the second inlet, and a base portion opening located in the base portion radially inward of the second inlet, wherein the first passage and the second passage extend through the base portion, the outlet portion, and the connection section; an orifice plug comprising: