The disclosure relates to a compressor for an exhaust gas turbocharger. The compressor includes a compressor wheel, a compressor housing having a volute and a diffuser, and a device for modifying the diffuser width. The device for modifying the diffuser is configured to automatically alter the diffuser width as a function of one or more current operating parameters of the compressor.

A centrifugal impeller shroud assembly has a dynamically moveable impeller shroud for encasing a rotatable centrifugal impeller and resolving misalignment between the impeller shroud and the rotatable centrifugal impeller. The assembly comprises a static casing, an impeller shroud, a shroud arm, and a thermal member. The shroud arm is coupled between the casing and the impeller shroud. The thermal member is coupled to the impeller shroud and has a coefficient of thermal expansion (CTE) lower than the CTE of the shroud. The shroud arm comprises a flexible portion configured to flex responsive to a differential pressure across the shroud arm.

A centrifugal impeller shroud assembly has a dynamically moveable impeller shroud for encasing a rotatable centrifugal impeller and resolving misalignment between the impeller shroud and the rotatable centrifugal impeller. The assembly comprises a static casing, an impeller shroud, a shroud arm, and a thermal member. The shroud arm is coupled between the casing and the impeller shroud. The thermal member is coupled to the impeller shroud and has a coefficient of thermal expansion (CTE) lower than the CTE of the shroud. The shroud arm comprises a flexible portion configured to flex responsive to a differential pressure across the shroud arm.

The gas turbine engine rotor can have a body having a solid-of-revolution-shaped portion centered around a rotation axis, the body defining an annular cavity centered around the rotation axis, the annular cavity penetrating into the body from an annular opening, the annular cavity extending between two opposite annular wall portions each leading to a corresponding edge of the opening; and at least one structural plate mounted to and extending between the two opposite annular wall portions and forming an interference fit therewith.

A high-efficiency compressor section (10) for a gas turbine engine is disclosed. The compressor section includes a vane carrier (12) adapted to hold ring segment assemblies (16) that provide optimized blade tip gaps (28,29) during a variety of operating conditions. The ring segment assemblies include backing elements (30) and tip-facing elements (32) urged into a preferred orientation by biasing elements (40) that maintain contact along engagement surfaces (44,46). The backing and tip-facing elements have thermal properties sufficiently different to allow relative growth that strategically forms an interface gap (42) therebetween, resulting in blade tip gaps that are dynamically adjusted operation.

A high-efficiency compressor section (10) for a gas turbine engine is disclosed. The compressor section includes a vane carrier (12) adapted to hold ring segment assemblies (16) that provide optimized blade tip gaps (28,29) during a variety of operating conditions. The ring segment assemblies include backing elements (30) and tip-facing, elements (32) urged into a preferred orientation by biasing elements (40) that maintain contact along engagement surfaces (44,46). The backing and tip-facing, elements have thermal properties sufficiently different to allow relative growth and geometric properties strategically selected to strategically form an interface gap therebetween (42) resulting in blade tip gaps that are dynamically adjusted operation.

A high-efficiency compressor section (10) for a gas turbine engine is disclosed. The compressor section includes a vane carrier (12) adapted to hold ring segment assemblies (16) that provide optimized blade tip gaps (28,29) during a variety of operating conditions. The ring segment assemblies include backing elements (30) and tip-facing elements (32) urged into a preferred orientation by biasing elements (40) that maintain contact along engagement surfaces (44,46). The backing and tip-facing elements have thermal properties sufficiently different to allow relative growth that strategically forms an interface gap (42,43) therebetween, resulting in blade tip gaps that are dynamically adjusted operation.

A high-efficiency compressor section (10) for a gas turbine engine is disclosed. The compressor section includes a vane carrier (12) adapted to hold ring segment assemblies (16) that provide optimized blade tip gaps (28,29) during a variety of operating conditions. The ring segment assemblies include backing elements (30) and tip-facing elements (32) urged into a preferred orientation by biasing elements (40) that maintain contact along engagement surfaces (44,46). The backing and tip-facing elements have thermal properties sufficiently different to allow relative growth and geometric properties strategically selected to strategically form an interface gap therebetween (42,43), resulting in blade tip gaps that are dynamically adjusted operation.