Pratt-whitney Canada Corp

Danny Mills

Eugene Gekht

Guy Bouchard

Keith Morgan

Lazar Mitrovic

Patrice Remy

Thomas Francis Haslam-Jones

Terrence Lucas

A rotor disk assembly comprises a first rotor disk with a plurality of circumferentially distributed first throughbores. A second rotor disk comprises a connection portion projecting at least partially axially, a plurality of circumferentially distributed second throughbores being provided in the connection portion in cooperative distribution relative to the first rotor disk for the first and second throughbores to be in register with one another in the rotor disk assembly. Connector bolts each have an elongated body with a flange between its ends, a head at its first end and a removable head at its second end, the head at the first end spaced apart from the flange for the connector bolt to be secured to one of the rotor disks at a respective throughbore, the removable head at the second end being spaced apart from the flange for the second end to project. An anti-rotation feature is between each said connector bolt and at least one of the rotor disks to prevent rotation of the connector bolts when the removable head is installed on the second end in the rotor disk assembly.

Fastening system for rotor hubs

A method for centering an engine structure such as a bearing housing is provided which may be used for example, during assembly of a mid turbine frame or other engine case structure. The method according to one embodiment may include machining spokes with an outer case of the mid turbine frame in situ to eliminate stack-up and then applying the retaining device to retain the spokes with respect to the outer case, thereby assuring the co-axial relationship between the outer case and the bearing housing supported within the mid turbine frame.

Engine structure assembly procedure

The method for forming a turbofan mixer comprises providing a single monolithic and generally flat annular sheet metal blank, providing a die surface substantially corresponding in shape to a turbofan mixer shape, positioning the blank with reference to the die surface, and forcing the blank against the die surface to transform the blank into a monolithic turbofan mixer.

Method and apparatus for forming a turbofan mixer

The described reduction gearbox of a gas turbine engine includes a first gear reduction stage having an input gear adapted to be driven by a turbine output shaft. The input gear transfers power received from the turbine output shaft laterally away from the input gear to an input speed gear. Each input speed gear engages an output speed gear to define a main speed reduction gear set, and the main speed reduction gear sets are laterally spaced apart from one another to define a gap. The gearbox has a second gear reduction stage driven by the output speed gears, the second stage adapted to drive an engine output shaft.

Reduction gearbox for a gas turbine engine

A gas turbine engine includes an annular plenum defined with an outer skin and a perforated inner skin for receiving selective air flow to impinge a support case which supports shrouds of the rotor assemblies of the engine therein for active tip clearance control of the rotor assemblies. In one embodiment a bobbin-type transfer tube for supplying cooling air into the plenum, is provided between an outer case of the engine an the plenum such that the thermally induced relative movement of the outer case and the plenum is permitted.

Active turbine or compressor tip clearance control

A stator vane segment, for constructing a circumferential array of like segments in a gas turbine engine, each segment in the array being separated by an axially extending joint from an adjacent segment and being releasably mounted to an outer engine casing. Each stator vane segment has: a number of vane airfoils spanning radially between an inner platform and an outer platform, and the outer platform includes: a casing mounting fastener on an outer surface and mating lateral joint edges extending between forward and aft edges.

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Chateauguay, Canada

Danny Mills