A fuel spray nozzle for generating a spray of atomised liquid fuel in a combustor of a gas turbine engine, wherein the fuel spray nozzle includes: a flow circuit having an inlet port for receiving a flow of liquid fuel and having an annular exit port for discharging the received fuel as a swirling fuel flow; and an annular prefilming surface downstream of the annular exit port, and configured such that the swirling fuel flow received from the exit port spreads, as a film of fuel, across the prefilming surface, whereupon one or more swirling air flows generated by the nozzle shear the fuel film towards a trailing edge of the prefilming surface and atomise the fuel film into a spray of fine droplets; wherein the flow circuit has in flow series: a gallery which wraps circumferentially around the nozzle and receives the fuel flow from the inlet port; plural circumferentially-spaced restrictor passages arranged in a row around the nozzle, the restrictor passages receiving respective portions of the fuel flow from the gallery; plural conditioning passages which respectively receive the portions of the fuel flow from the restrictor passages and are configured to impart a circumferential component to their respective portions of the fuel flow; and an annular spin chamber which receives and recombines the respective portions of the fuel flow from the conditioning passages to form the swirling fuel flow which is discharged at the exit port; wherein: the restrictor passages form flow restrictions which in use produce a pressure differential between the gallery and the spin chamber to evenly circumferentially distribute the fuel flow between the restrictor passages; and the conditioning passages have increased flow cross-sectional areas relative to the flow cross-sectional areas of the restrictor passages, such that the restrictor passages produce substantially all of the pressure differential between the gallery and the spin chamber. a flow circuit having an inlet port for receiving a flow of liquid fuel and having an annular exit port for discharging the received fuel as a swirling fuel flow; and an annular prefilming surface downstream of the annular exit port, and configured such that the swirling fuel flow received from the exit port spreads, as a film of fuel, across the prefilming surface, whereupon one or more swirling air flows generated by the nozzle shear the fuel film towards a trailing edge of the prefilming surface and atomise the fuel film into a spray of fine droplets; wherein the flow circuit has in flow series: a gallery which wraps circumferentially around the nozzle and receives the fuel flow from the inlet port; plural circumferentially-spaced restrictor passages arranged in a row around the nozzle, the restrictor passages receiving respective portions of the fuel flow from the gallery; plural conditioning passages which respectively receive the portions of the fuel flow from the restrictor passages and are configured to impart a circumferential component to their respective portions of the fuel flow; and an annular spin chamber which receives and recombines the respective portions of the fuel flow from the conditioning passages to form the swirling fuel flow which is discharged at the exit port; a gallery which wraps circumferentially around the nozzle and receives the fuel flow from the inlet port; plural circumferentially-spaced restrictor passages arranged in a row around the nozzle, the restrictor passages receiving respective portions of the fuel flow from the gallery; plural conditioning passages which respectively receive the portions of the fuel flow from the restrictor passages and are configured to impart a circumferential component to their respective portions of the fuel flow; and an annular spin chamber which receives and recombines the respective portions of the fuel flow from the conditioning passages to form the swirling fuel flow which is discharged at the exit port; wherein: the restrictor passages form flow restrictions which in use produce a pressure differential between the gallery and the spin chamber to evenly circumferentially distribute the fuel flow between the restrictor passages; and the conditioning passages have increased flow cross-sectional areas relative to the flow cross-sectional areas of the restrictor passages, such that the restrictor passages produce substantially all of the pressure differential between the gallery and the spin chamber. the restrictor passages form flow restrictions which in use produce a pressure differential between the gallery and the spin chamber to evenly circumferentially distribute the fuel flow between the restrictor passages; and the conditioning passages have increased flow cross-sectional areas relative to the flow cross-sectional areas of the restrictor passages, such that the restrictor passages produce substantially all of the pressure differential between the gallery and the spin chamber.