Air circuit for aircraft propulsion system

An assembly for an aircraft propulsion system, comprising:

• a compressor section;
• a combustor section;
• a turbine section;
• a core flowpath extending axially along an axis and through the compressor section, the combustor section and the turbine section;
• a bypass flowpath extending axially along the axis and bypassing at least one of the compressor section, the combustor section or the turbine section;
• a flowpath wall forming an inner peripheral boundary of the bypass flowpath, the flowpath wall including a wall base and a wall protrusion, the wall base extending axially along and circumferentially around the axis, the wall protrusion projecting radially out from the wall base at an intermediate position axially along the wall base, the wall protrusion extending axially along the axis from a protrusion first end to a protrusion second end, the protrusion first end upstream of the protrusion second end along the bypass flowpath, and the wall protrusion extending at least thirty degrees circumferentially about the axis;
• and
• an air circuit extending from a circuit inlet to a circuit outlet, the circuit inlet fluidly coupled to the core flowpath upstream of a combustor in the combustor section, the circuit outlet fluidly coupled to the bypass flowpath, and the circuit outlet formed in the wall protrusion axially between the protrusion first end and the protrusion second end.

An assembly for an aircraft propulsion system, comprising:

• a compressor section;
• a combustor section;
• a turbine section;
• a core flowpath extending axially along an axis and through the compressor section, the combustor section and the turbine section;
• a bypass flowpath extending axially along the axis and bypassing at least one of the compressor section, the combustor section or the turbine section;
• a flowpath wall forming an inner peripheral boundary of the bypass flowpath, the flowpath wall including a wall base and a wall protrusion, the wall base extending axially along and circumferentially around the axis, the wall protrusion projecting radially out from the wall base at an intermediate position axially along the wall base, the wall protrusion extending axially along the axis from a protrusion first end to a protrusion second end, the protrusion first end upstream of the protrusion second end along the bypass flowpath, and the wall protrusion extending at least thirty degrees circumferentially about the axis;
• and
• an air circuit extending from a circuit inlet to a circuit outlet, the circuit inlet fluidly coupled to the core flowpath upstream of a combustor in the combustor section, the circuit outlet fluidly coupled to the bypass flowpath and formed in the wall protrusion;
• a first end section of the wall protrusion tapering to the wall base as the first end section projects axially to the protrusion first end;
• and
• a second end section of the wall protrusion tapering to the wall base as the second end section projects axially to the protrusion second end.