Abstract: A gas turbine engine includes a spool, a turbine coupled to drive the spool and a propulsor that is coupled to be driven by the turbine through the spool. A gear assembly is coupled between the propulsor and the spool such that rotation of the spool drives the propulsor at a different speed than the spool. The propulsor includes a hub and a row of propulsor blades that extends from the hub. The row includes no more than 16 of the propulsor blades.

Abstract: A rotor has a central shaft having a central longitudinal axis. The rotor has a longitudinal stack of a plurality of disks surrounding the shaft. An aft hub couples the stack to the shaft. The aft hub has a proximal portion and a distal portion. The distal portion tapers at a lower characteristic half angle than does the proximal portion.

Abstract: A gas turbine engine rotor drum includes spaced apart discs providing a cavity between the discs. The discs are configured to rotate in a rotational direction about an axis. An annular support is mounted on at least one of the discs and within the cavity. A cascade of relatively short anti-vortex members is mounted circumferentially on the annular support. The anti-vortex members include an outer end having a concave surface extending within the cavity radially outward from the annular support. The concave surface faces the rotational direction and promotes swirl as the rotor drum rotates.

Abstract: A gas turbine engine rotor drum includes spaced apart discs providing a cavity between the discs. The discs are configured to rotate in a rotational direction about an axis. An annular support is mounted on at least one of the discs and within the cavity. A cascade of relatively short anti-vortex members is mounted circumferentially on the annular support. The anti-vortex members include an outer end having a concave surface extending within the cavity radially outward from the annular support. The concave surface faces the rotational direction and promotes swirl as the rotor drum rotates.

Abstract: A gas turbine engine includes a bleed structure which includes a forward wall and a rear structural wall to define a deposit space downstream of the bleed structure for a hail event of a predetermined duration.

Abstract: A gas turbine engine rotor drum includes spaced apart discs providing a cavity between the discs. The discs are configured to rotate in a rotational direction about an axis. An annular support is mounted on at least one of the discs and within the cavity. A cascade of relatively short anti-vortex members is mounted circumferentially on the annular support. The anti-vortex members include an outer end having a concave surface extending within the cavity radially outward from the annular support. The concave surface faces the rotational direction and promotes swirl as the rotor drum rotates.

Abstract: A rotor has a central shaft having a central longitudinal axis. The rotor has a longitudinal stack of a plurality of disks surrounding the shaft. An aft hub couples the stack to the shaft. The aft hub has a proximal portion and a distal portion. The distal portion tapers at a lower characteristic half angle than does the proximal portion.

Abstract: The present invention relates to a bumper system for use with a compressor variable vane system. The bumper system broadly comprises a synchronizing ring, a bumper, a shim for defining a gap between a bumper pad and the bumper, a pin for preventing rotation of the bumper relative to the synchronizing ring, and a device for fully trapping the shim. In a first embodiment, the device for fully trapping the shim comprises a sleeve passing through the synchronizing ring. In a second embodiment, the device for fully trapping the shim comprises a pin which passes through the synchronizing body. In a third embodiment, the device for fully trapping the shim comprises a fastener with a shoulder.

Abstract: The present invention relates to a bumper system for use with a compressor variable vane system. The bumper system broadly comprises a synchronizing ring, a bumper, a shim for defining a gap between a bumper pad and the bumper, a pin for preventing rotation of the bumper relative to the synchronizing ring, and a device for fully trapping the shim. In a first embodiment, the device for fully trapping the shim comprises a sleeve passing through the synchronizing ring. In a second embodiment, the device for fully trapping the shim comprises a pin which passes through the synchronizing body. In a third embodiment, the device for fully trapping the shim comprises a fastener with a shoulder.