The invention provides a pilot nozzle for a gas turbine combustion device for improving a flame retaining effect. In the pilot nozzle 1, a gas fuel passage 2 provided in parallel with an axis is bent slantingly outward in an end part 3. Thus, the pilot nozzle 1 jets diffused fuel slantingly forward to form a flame 4. In the outlet of a fuel jet port, a cylindrical flow separating body 5 is provided at a central part as apparent in Figture A viewed from the above. Combustion gas upon combustion of fuel circulates near the outlet of the fuel jet port as shown by arrows 6 by a flow of fuel jetted to avoid the flow separating body 5. Thus, the root of the flame is stabilized and the flame can be prevented from being blown out by air flowing from an upstream side. |