Abstract: A support plate for an engine casing includes an anti-rotation rib abutting an outer flange wall of the casing and a misalignment tab extending radially outwardly from the anti-rotation rib. The support plate has a support plate hole configured to be aligned with one flange hole of a flange of the casing.

Abstract: A tool for shaping an abradable liner of a turbofan engine is disclosed. The turbofan engine includes a shaft to support a fan rotatable about a rotation axis. The abradable liner is configured to surround the fan and has an axial length in the direction of the rotation axis. The tool includes a support configured to be mounted to the shaft and rotatable about the rotation axis. The shaping head is mounted to the support for rotation about the rotation axis and configured to shape the abradable liner by removing material from the abradable liner. A radial position of the shaping head is adjustable relative to the rotation axis. The shaping head may sized to extend substantially across the axial length of the abradable liner.

Abstract: A vane assembly adapted to be disposed through an annular gas flow path defined between a fan case and an engine core of a gas turbine engine. The assembly comprises a vane having a vane body configured for extending between the engine core and the fan case, a vane head disposed at one end of the vane body, the vane head being adapted to be disposed outside the annular gas flow path, the vane head having an abutting surface configured for contacting an outer surface of the fan case, and a recess extending within the vane head and opening to the abutting surface. The recess is configured for circumferentially surrounding a longitudinal axis of the vane and forming a closed figure. The assembly also comprises a sealing member disposed within the recess.

Abstract: A turbofan engine is disclosed having a bypass duct with an asymmetry in aerodynamic profile caused by a local obstruction in the bypass duct. The engine comprises stator vanes circumferentially spaced-apart around a circumference of the bypass duct. A first group of adjacent stator vanes includes a majority of the plurality of stator vanes and are arranged in a first circumferential sector of the bypass duct and have equal stagger angles. A second group of adjacent stator vanes includes a minority of the plurality of stator vanes and are arranged in a second circumferential sector circumferentially positioned relative to the local obstruction. The stator vanes of the second group have stagger angles different from the stagger angles of the stator vanes of the first group.

Abstract: A seal spacer for a gas turbine engine to provide sealing between a casing wall and a stator vane of the engine. The seal spacer comprises a circumferential body having a slot defined therethrough and configured to receive the stator vane therein. The circumferential body is configured to be disposed between and space apart the engine casing wall from a head of the stator vane when the vane is inserted in the slot and the vane is inserted in the opening in the casing wall. The circumferential body includes a support positioned to be engage and provide a gap between the casing wall and the head when the seal spacer is installed therebetween, and an elastomeric seal portion positioned to engage and compressingly provide sealing the casing wall and the head when the seal spacer is installed therebetween to seal the gap.

Abstract: A seal spacer for a gas turbine engine to provide sealing between a casing wall and a stator vane of the engine. The seal spacer comprises a circumferential body having a slot defined therethrough and configured to receive the stator vane therein. The circumferential body is configured to be disposed between and space apart the engine casing wall from a head of the stator vane when the vane is inserted in the slot and the vane is inserted in the opening in the casing wall. The circumferential body includes a support positioned to be engage and provide a gap between the casing wall and the head when the seal spacer is installed therebetween, and an elastomeric seal portion positioned to engage and compressingly provide sealing the casing wall and the head when the seal spacer is installed therebetween to seal the gap.

Abstract: A vane assembly adapted to be disposed through an annular gas flow path defined between a fan case and an engine core of a gas turbine engine. The assembly comprises a vane having a vane body configured for extending between the engine core and the fan case, a vane head disposed at one end of the vane body, the vane head being adapted to be disposed outside the annular gas flow path, the vane head having an abutting surface configured for contacting an outer surface of the fan case, and a recess extending within the vane head and opening to the abutting surface. The recess is configured for circumferentially surrounding a longitudinal axis of the vane and forming a closed figure. The assembly also comprises a sealing member disposed within the recess.

Abstract: A turbofan engine is disclosed having a bypass duct with an asymmetry in aerodynamic profile caused by a local obstruction in the bypass duct. The engine comprises stator vanes circumferentially spaced-apart around a circumference of the bypass duct. A first group of adjacent stator vanes includes a majority of the plurality of stator vanes and are arranged in a first circumferential sector of the bypass duct and have equal stagger angles. A second group of adjacent stator vanes includes a minority of the plurality of stator vanes and are arranged in a second circumferential sector circumferentially positioned relative to the local obstruction. The stator vanes of the second group have stagger angles different from the stagger angles of the stator vanes of the first group.