Methods and apparatus to provide cross-diffuser bleed

A diffuser for routing a bleed air within a gas turbine engine, the diffuser comprising:

• an inner shell;
• an outer shell;
• and
• a plurality of surfaces between the inner shell and the outer shell, the plurality of surfaces defining a plurality of discrete passageways, a first conduit and a second conduit positioned between directly consecutive passageways of the plurality of discrete passageways, the first conduit and the second conduit fluidly connected to a cavity positioned on a first side of the diffuser, and the first conduit and the second conduit fluidly connected to a downstream sink positioned on a second side of the diffuser, the first conduit and the second conduit defining at least a portion of a bleed air path, and the first conduit has a greater cross-sectional area than the second conduit.

A bleed air system for an aircraft, the bleed air system comprising:

• a frame defining a cavity;
• a diffuser to provide air to a combustor via a primary flow path, the diffuser including:
• at least one diffuser vane in the primary flow path;
• and
• a first conduit and a second conduit in the at least one diffuser vane, the first conduit and the second conduit fluidly coupled to the cavity, the first conduit and the second conduit defining at least a portion of a bleed air path through the at least one diffuser vane, the first conduit has a greater cross-sectional area than the second conduit;
• a passage coupled to the first conduit and the second conduit at a first end of the passage;
• and
• a downstream sink coupled to the passage at a second end of the passage, the downstream sink fluidly coupled to the cavity via the first conduit, the second conduit, and the passage.