Compressor bleed slot diffuser

A gas turbine engine comprising:

• an engine core defining an engine axis and having a compressor section, a combustor section, and a turbine section arranged along the engine axis, with a core flow in a core flow path defined through the compressor section, the combustor section, and the turbine section;
• a casing of the compressor section defining, in part, a portion of the core flow path, with a bleed air cavity defined between the casing of the compressor section and an engine housing;
• an impeller arranged between the compressor section and the combustor section along the core flow path, the impeller comprising an impeller shroud, wherein the impeller is configured to receive the core flow from the compressor section at an inlet to the impeller and direct a combustor portion of the core flow to the combustor section;
• a bleed aperture defined axially between the casing and the impeller shroud, wherein the bleed aperture is defined as a circumferential slot that is substantially continuous about a circumference of the engine core;
• and
• a bleed flow extension extending from the casing and into the bleed air cavity, wherein the bleed flow extension is a circumferential structure extending from an edge of the casing that defines a forward edge of the bleed aperture,
• wherein a diffuser channel is defined between an upstream wall defined by a surface of the bleed flow extension along a forward side of the diffuser channel and a downstream wall defined by a surface of the impeller shroud opposite a surface of the impeller shroud that defines a portion of the core flow path along an aft side of the diffuser channel,
• wherein the diffuser channel has an inlet area that is less than an outlet area,
• wherein the combustor portion of the core flow received at the inlet to the impeller is compressed and turned from an axial flow direction to a radial flow direction and then directed into the combustor and wherein a bleed air portion of the core flow received at the inlet to the impeller is separated from the combustor portion at the bleed aperture and directed through the diffuser channel and into the bleed air cavity.