Pratt-whitney Canada Corp

Alexander Smith

Christopher Gover

Gabriel Naccache

Alain C Martel

Matthieu Boudreau

Pierre-Yves Legare

Vincent Paradis

Marc-Antoine Mailloux-Labrousse

Acher-Igal Abenhaim

Haw On Tam

A tangential on-board injector (TOBI), comprising: a body defining an annular passageway to receive cooling air, the TOBI defining a plurality of discharge nozzles; a rotating component mounted for rotation relative to the body about an axis of rotation; a seal extending between the body and the rotating component; a plurality of vanes circumferentially distributed about the axis of rotation and located downstream of the plurality of discharge nozzles relative to a flow of the cooling air circulating toward the seal from the plurality of discharge nozzles and upstream of the seal; and flow passages defined between the plurality of vanes, a flow passage of the flow passages extending along a passage axis, the passage axis having a tangential component at an outlet of the flow passage that is different than a tangential component of an exit flow axis of a nozzle of the plurality of discharge nozzles.

Tangential on-board injector (TOBI) assembly

A tangential on-board injector (TOBI) having: a body defining an annular passageway, discharge nozzles; a rotating component configured to be mounted for rotation relative to the body about an axis of rotation; a seal extending between the body and the rotating component; and flow passages circumferentially distributed about the axis of rotation and in fluid communication with the nozzles and the seal, the flow passages located upstream of the seal relative to a flow of the cooling air circulating toward the seal from the plurality of discharge nozzles, each of the flow passages extending along a respective passage axis, the passage axis of at least one of the flow passages having a tangential component at an outlet of the at least one of the flow passages that is different than a tangential component of an exit flow axis of at least one of the plurality of discharge nozzles.

A gas turbine engine comprising: a shaft about an axis; a first turbine assembly mounted to the shaft, a first flow path and a second flow path extending through first turbine assembly along the axis. The second flow path is located radially inward of the first flow path relative to the axis. A second turbine assembly is about the axis downstream of the first turbine assembly, with a gap defined between the first turbine assembly and the second turbine assembly, the gap in fluid communication with the first flow path and the second flow path. A washer is downstream of the first turbine assembly. The washer has an annular body including a deflector between the first turbine assembly and the second turbine assembly, the deflector obstructing the first flow path and extending toward the second flow path.

Key washer for a gas turbine engine

An aircraft engine having a shaft, an engine casing, at least one bearing located between the shaft and the engine casing, the engine casing defining a bearing cavity containing the at least one bearing, an air distribution system configured to inject compressed air to the bearing cavity to in use provide a sealing air flow entering the bearing cavity, and a labyrinth seal having a seal rotor and a seal stator, fins extending from one of the seal rotor and the seal stator toward the other of the seal rotor and the seal stator, at least one of the fins extending in an angled upstream direction relative to a direction of the sealing air flow.

Labyrinth seal with angled fins

There is provided a non-contacting seal assembly for a gas turbine engine, having a housing that houses a sealing ring; and a counter component cooperating with the sealing ring. The sealing ring and the counter component are rotatable relative to each other about a central axis and define sealing faces circumferentially extending around the central axis. The sealing faces face each other and are spaced apart from each other by a controlled gap. At least one of the sealing faces is coated with a non-abradable material. A method of operating a non-contacting seal assembly is also provided.

Non-contacting seal with non-abradable coating

An inner ring for a bearing assembly with an inner surface having a plurality of circumferentially spaced axial slots defined therein each having a flat axially extending bottom wall and a plurality of circumferentially spaced partial circumferential slots defined therein each intersecting one of the axial slots and extending circumferentially therefrom around a respective portion of a circumference of the inner surface, shoulder radial holes extending therethrough each from a respective one of the circumferential slots to a corresponding one of the shoulders, and race radial holes extending therethrough each from a respective one of the circumferential slots to a corresponding corner of the inner race. The radial holes are circumferentially offset from the axial slots. A bearing assembly and a method of lubricating such an assembly are also discussed.

Growing community of inventors

Montreal, Canada

Alexander Smith