GAS TURBINE COMPRESSOR RADIAL DOOR BLEED VALVE

A bleed system of a gas turbine engine (20) includes a bleed duct (66) having a duct inlet (70) located at a flowpath of a gas turbine engine (20), and a bleed outlet (72) located outside of the flowpath, and extending circumferentially around a central longitudinal axis. A plurality of bleed doors (86) are located at the bleed outlet (72) and are arrayed along a circumferential length on the bleed duct (66). Each bleed door (86) includes a first circumferential end (92), and a second circumferential end (94). The bleed doors (86) are arrayed such that when the bleed doors (86) are in a closed position the first circumferential end (92) is located at the second circumferential end (94) of an adjacent bleed door (86) of the bleed doors (86). Each bleed door (86) includes a pivot (104), such that each bleed door (86) rotates about the pivot (104) from the closed position covering the duct outlet (72) to an opened position allowing a bleed airflow to pass through the duct outlet (72).