Housing for a centrifugal compressor

An impeller housing for an impeller of a centrifugal compressor of a gas turbine engine, comprising:

• a shroud annularly extending around a central axis, the shroud having a gaspath side facing the central axis and an opposed rear side, the shroud having a first end proximate an inlet of the impeller and a second end proximate an outlet of the compressor;
• a structural member supporting the shroud, the structural member having an outer end securable to a casing of the gas turbine engine, an inner end of the structural member intersecting the rear side of the shroud at a location between the first end and the second end, a portion of the shroud extending radially outwardly from the location, the portion being cantilevered from the structural member;
• and
• a reinforced region at the location where the structural member and the rear side of the shroud intersect, the portion of the shroud supported solely at the reinforced region, a thickness of the reinforced region in a direction normal to the gaspath side greater than a nominal thickness of the shroud outside the reinforced region, the reinforced region extending from a first location on the structural member to a second location on the rear side of the shroud, the second location between the structural member and the second end, the thickness of the reinforced region increasing from the nominal thickness at the second location towards the structural member,
• a ratio of a radial distance (D3) relative to the central axis from the second end to the second location to a radial height (H1) of a portion of the shroud that extends radially outwardly beyond the inner end of the structural member being at most 0.8.

A centrifugal compressor for a gas turbine engine, comprising:

• an impeller having blades extending from a hub to blade tips, the impeller having an inlet and an outlet;
• and
• a housing disposed around the impeller, the impeller rotatable relative to the housing about a central axis, the housing including:
• a shroud annularly extending around the blade tips of the impeller and extending in a streamwise direction between a first end proximate the inlet of the impeller and a second end proximate the outlet of the impeller, the shroud having a gaspath side facing the impeller and a rear side opposed to the gaspath side;
• a structural member supporting the shroud, the structural member having an outer end securable to a casing of the gas turbine engine, an inner end of the structural member intersecting the rear side of the shroud at a location between the first end and the second end, a portion of the shroud extending radially outwardly from the location, the portion being cantilevered from the structural member;
• and
• a reinforced region at the location where the structural member and the rear side of the shroud intersect, the reinforced region annularly extending around the central axis, the portion of the shroud supported solely at the reinforced region, a thickness of the reinforced region in a direction normal to the gaspath side being greater than a nominal thickness of the shroud outside the reinforced region, the reinforced region defining a curved surface extending from a first location on the structural member to a second location on the rear side of the shroud, the second location being disposed between the structural member and the second end of the shroud, a portion of the curved surface having a radius that increases from a first radius to a second radius at the second location, the second location being closer to the second end than to the inner end of the structural member.