Abstract: A gas turbine engine includes a bypass duct extending about a longitudinal centerline of the gas turbine engine. The bypass duct includes at least one bypass duct wall defining at least a portion of a bypass flow path through the bypass duct. The at least one bypass duct wall includes a scoop extending into the bypass flow path. The gas turbine engine further includes a bleed conduit including an inlet connected to the bypass duct within the scoop of the at least one bypass duct wall and at least one louver mounted to the bleed conduit within the inlet. The at least one louver extends between a leading edge and a trailing edge opposite the leading edge. The leading edge is located within the bypass flow path and the trailing edge is located within the bleed conduit.

Abstract: A system is provided for a gas turbine engine. This gas turbine engine system includes a flowpath wall and a deflector. The flowpath wall includes a surface and an opening to a blind aperture. The surface forms a peripheral boundary of an internal engine flowpath. The opening is disposed in the surface. The blind aperture extends vertically into the flowpath wall from the opening. The deflector projects vertically out from the flowpath wall into the internal engine flowpath. The deflector is configured to deflect gas flowing within the internal engine flowpath over the opening.

Abstract: A system is provided for a gas turbine engine. This gas turbine engine system includes a flowpath wall and a deflector. The flowpath wall includes a surface and an opening to a blind aperture. The surface forms a peripheral boundary of an internal engine flowpath. The opening is disposed in the surface. The blind aperture extends vertically into the flowpath wall from the opening. The deflector projects vertically out from the flowpath wall into the internal engine flowpath. The deflector is configured to deflect gas flowing within the internal engine flowpath over the opening.

Abstract: A gas turbine engine includes a bypass duct extending about a longitudinal centerline of the gas turbine engine. The bypass duct includes at least one bypass duct wall defining at least a portion of a bypass flow path through the bypass duct. The at least one bypass duct wall includes a scoop extending into the bypass flow path. The gas turbine engine further includes a bleed conduit including an inlet connected to the bypass duct within the scoop of the at least one bypass duct wall and at least one louver mounted to the bleed conduit within the inlet. The at least one louver extends between a leading edge and a trailing edge opposite the leading edge. The leading edge is located within the bypass flow path and the trailing edge is located within the bleed conduit.

Abstract: An aircraft engine, has: a duct having an inlet, an outlet, and a bleed port through a wall of the duct; a bleed conduit stemming from the duct; a first valve connected to the bleed conduit and having an open configuration and a closed configuration; and a second valve connected to the bleed conduit upstream of the first valve and at or proximate the bleed port, the second valve having a second open configuration and a second closed configuration, when in the second closed configuration, the second valve blocking fluid communication between the bleed port and the first valve such that a portion of the bleed conduit between the first valve and the second valve is fluidly isolated from the duct, the second valve being in the second open configuration when the first valve is in the open configuration.