A fuel spray apparatus for a gas turbine engine, adapted to mix fuel with compressed air supplied from a compressor of the gas turbine engine and then combust the fuel with the supplied compressed air, comprising: a pilot part configured to spray fuel to be used for a diffusion combustion; a main part provided so as to surround the pilot part and configured to inject a pre-mixed gas only upon a high power operation; and a shield body constituting a purge air passage which is configured to take therein the compressed air flowed on an upstream side relative to a fuel injection port of the main part as a purge air, and to blow off a fuel dripping from the fuel injection port toward a main air passage (37, 42) of the main part, wherein the purge air passage is provided in a position opposite to a main fuel passage communicated with the fuel injection port across the shield body, and characterised in that: the fuel spray apparatus for the gas turbine engine further comprises a shroud covering the main fuel passage and the shield body, wherein the shroud is provided with an intake port and a discharge port for the purge air, and wherein the purge air passage is provided between an inner face of an outer circumferential wall of the shroud and the shield body, that the shroud covers a fuel passage via a heat insulating space, wherein a pilot fuel passage and the main fuel passage are provided in the fuel passage, and that the pilot fuel passage is provided adjacent to the main fuel passage such that a main fuel can be cooled with a pilot fuel. a pilot part configured to spray fuel to be used for a diffusion combustion; a main part provided so as to surround the pilot part and configured to inject a pre-mixed gas only upon a high power operation; and a shield body constituting a purge air passage which is configured to take therein the compressed air flowed on an upstream side relative to a fuel injection port of the main part as a purge air, and to blow off a fuel dripping from the fuel injection port toward a main air passage (37, 42) of the main part, wherein the purge air passage is provided in a position opposite to a main fuel passage communicated with the fuel injection port across the shield body, and characterised in that: the fuel spray apparatus for the gas turbine engine further comprises a shroud covering the main fuel passage and the shield body, wherein the shroud is provided with an intake port and a discharge port for the purge air, and wherein the purge air passage is provided between an inner face of an outer circumferential wall of the shroud and the shield body, that the shroud covers a fuel passage via a heat insulating space, wherein a pilot fuel passage and the main fuel passage are provided in the fuel passage, and that the pilot fuel passage is provided adjacent to the main fuel passage such that a main fuel can be cooled with a pilot fuel. the fuel spray apparatus for the gas turbine engine further comprises a shroud covering the main fuel passage and the shield body, wherein the shroud is provided with an intake port and a discharge port for the purge air, and wherein the purge air passage is provided between an inner face of an outer circumferential wall of the shroud and the shield body, that the shroud covers a fuel passage via a heat insulating space, wherein a pilot fuel passage and the main fuel passage are provided in the fuel passage, and that the pilot fuel passage is provided adjacent to the main fuel passage such that a main fuel can be cooled with a pilot fuel.