Impeller back-face cooling manifold

A compressor section of a gas turbine engine of an aircraft, the compressor section comprising:

• an impeller;
• a diffuser baffle defining holes arranged about an engine centerline, the diffuser baffle being disposed proximate to the impeller whereby the impeller and the diffuser baffle define an intervening cavity therebetween;
• a cooling manifold attached to the diffuser baffle and configured to distribute coolant along a plane of the diffuser baffle such that the coolant is directed through each of the holes and tangentially toward the impeller;
• and
• piping extending through the diffuser baffle and terminating at the cooling manifold to deliver the coolant to the cooling manifold,
• wherein the cooling manifold comprises:
• an interior body comprising an interior body surface and an elongate, solid body extending from the interior body surface and defining through-vias, each through-via being aligned with a corresponding one of the holes;
• and
• an exterior body configured to surround the interior body to form a cavity, which is fluidly communicative with the through-vias, between the exterior body and the interior body, and
• the interior body and the exterior body being annular about an engine centerline and the exterior body comprising an annular outboard portion with a radially inwardly curving distal end outboard of the interior body, an annular inboard portion with a radially outwardly curving distal end inboard of the interior body and an annular connecting portion extending between the respective distal ends of the annular outboard and inboard portions and defining one or more apertures as multiple apertures arranged about the engine centerline by which the cavity is receptive of the coolant such that the coolant is distributed throughout the cavity and exhausted tangentially through each of the one or more through-vias.

A compressor section of a gas turbine engine of an aircraft, the compressor section comprising:

• an impeller comprising an impeller front-face along which high-temperature air flows and an impeller back-face opposite the impeller front-face;
• a diffuser baffle comprising a sheet element defining holes arranged about an engine centerline, the diffuser baffle being disposed proximate to the impeller whereby the impeller and the sheet element define an intervening cavity therebetween;
• a cooling manifold attached to the sheet element and configured to distribute coolant along a plane of the diffuser baffle such that the coolant is directed through each of the holes and tangentially toward the impeller;
• and
• piping extending through the diffuser baffle and terminating at the cooling manifold to deliver the coolant to the cooling manifold,
• wherein the cooling manifold comprises:
• an interior body comprising an interior body surface and an elongate, solid body extending from the interior body surface and defining through-vias, each through-via being aligned with a corresponding one of the holes;
• and
• an exterior body configured to surround the interior body to form a cavity, which is fluidly communicative with the through-vias, between the exterior body and the interior body, and
• the interior body and the exterior body being annular about an engine centerline and the exterior body comprising an annular outboard portion with a radially inwardly curving distal end outboard of the interior body, an annular inboard portion with a radially outwardly curving distal end inboard of the interior body and an annular connecting portion extending between the respective distal ends of the annular outboard and inboard portions and defining one or more apertures as multiple apertures arranged about the engine centerline by which the cavity is receptive of the coolant such that the coolant is distributed throughout the cavity and exhausted tangentially through each of the one or more through-vias.