The invention relates to a method for introducing a balancing mark into the compressor wheel of a turbocharger. According to the method, a milling tool is firstly moved in a first direction in order to introduce a recess into the compressor wheel, and the milling tool located in the recess then runs out in a second direction in order to convert the recess into a pear segment-shaped balancing mark. The invention furthermore relates to a turbocharger which comprises a compressor wheel that has one or more pear segment-shaped balancing marks.

A control system and method utilizing one or more processors that are configured to determine contaminant loading of blades of a turbomachinery compressor based on one or more environmental conditions to which the turbomachinery compressor is exposed and one or more atmospheric air inlet conditions of the turbomachinery compressor. The one or more processors then determine a corrosion contaminant concentration on the blades of the turbomachinery compressor based on the contaminant loading that is determined and determine an upper limit on or a distribution of potential corrosion of the blades of the turbomachinery based on the corrosion contaminant concentration, at least one of the environmental conditions to which the turbomachinery compressor is exposed, and the corrosion contaminant concentration that is determined.

Seal (10) for an inter-blade platform intended to extend circumferentially about an axis and to be mounted between two axial ends of the inter-blade platform, including a first part (10a) in contact with a first blade adjacent to a first circumferential end of the platform, and a second part (10b) in contact with a second blade adjacent to a second circumferential end of the platform, the first part (10a) and the second part (10b) of the seal (10) being fixed to each other such that a displacement in the circumferential direction of one of the two parts (10a, 10b) of the seal (10) causes a displacement of the other part (10a, 10b) of the seal (10) in the same direction, when the two parts (10a, 10b) of the seal (10) are fixed to each other.

A rotor assembly has a drive shaft and a bladed rotor mounted to the drive shaft for rotation therewith. A dampening material is bonded to the rotor at a location where there is torsional strain energy present. Shear forces in the damping material are used to convert the torsional strain energy into heat energy, thereby providing torsional vibration damping.

One embodiment is a rotor system including a rotor hub comprising a plurality of extension arms for connecting rotor blades to the rotor hub; a plurality of dampers connected between a respective one of the extension arms and the rotor hub; and a fairing disposed over the rotor hub, the fairing including an inlet plenum through which air is drawn from outside the fairing into the fairing; and at least one duct for conducting the air toward the at least one of the dampers.

A propeller, impeller or mixer comprising at least one blade, the blade having a suction surface and a pressure surface which extend from a leading edge to a trailing edge of the blade and a radially-outer tip region, wherein five to one hundred duct openings are provided extending through the at least one blade from the pressure surface to the suction surface, the duct openings being grouped in the tip region of the blade.

A sealing structure for a gas turbine includes a turbine rotor disk, a turbine blade coupled the turbine rotor disk, and an interstage disk interposed between adjacent turbine rotor disks. The turbine blade includes a blade circumferential surface protruding axially and extending in a circumferential direction of the turbine rotor disk and mutually engaging with a disk circumferential surface formed circumferentially on the turbine rotor disk. The interstage disk includes a rim portion and a groove formed in the rim portion. A plurality of static ring seals are mounted in the groove, each static ring seal facing toward the blade circumferential surface and the disk circumferential surface. The static ring are configured such that an outer circumferential surface of all the static ring seals contact the blade circumferential surface and the outer circumferential surface of at least one of the static ring seals does not contact the disk circumferential surface.

A seal device includes a plurality of seal shoes, a seal base, a plurality of spring elements and a resilient biasing element. The seal shoes are arranged around an axis. The seal base circumscribes the seal shoes. Each of the spring elements is radially between and connects a respective one of the seal shoes and the seal base. A first of the spring elements includes a first mount, a second mount and a spring beam. The first mount is connected to a first of the seal shoes. The second mount is connected to the seal base. The spring beam connects the first mount to the second mount. The resilient biasing element is radially between and engaged with first and second components of the seal device, where the first component is configured as or otherwise includes the first mount or the second mount.

An air-sending device includes a propeller fan, a bell mouth surrounding an outer periphery of the propeller fan, a fan grille disposed downstream of the bell mouth and including a plurality of first crosspieces. An edge of the air outlet of the bell mouth includes a varying portion whose distance from a rotation axis of the propeller fan varies. In a cross-section of any of the plurality of first crosspieces that is perpendicular to a longitudinal direction of the any of the plurality of first crosspieces, a virtual line segment connecting an upstream side end portion and a downstream side end portion is defined as a first virtual line segment. At the portions of the plurality of first crosspieces disposed on the inner circumference side of the varying portion, the angle between a virtual line segment parallel to the rotation axis and the first virtual line segment is changed.

A fan rotor includes a fan hub and a plurality of fan blades extending radially outwardly from the fan hub. Platforms are positioned intermediate blade sides of adjacent ones of the fan blades. Seals are positioned between the blade sides and platform sides of the platform seals. The seals have an elongated bonding area bonded to one of the platform sides and the fan blade sides. The seal extends radially outwardly from the elongated bonding area to a wedge portion. A gas turbine engine and a seal are also disclosed.