Patent attributes
A gas turbine engine includes a compressor section having multiple stages, a combustor section fluidly connected to the compressor section, a turbine section fluidly connected to the combustor section, and a bleed structure radially outward of the stages. The bleed structure includes a body structure having a first set of openings radially outward of a first stage and a second set of openings radially outward of a second stage. The bleed structure further includes a circumferential sleeve configured to cover the first set of openings in a first position and configured to cover the second set of openings in a second position. An actuator is coupled to the circumferential sleeve and is configured to articulate the sleeve between the first and second positions.
