Pratt-whitney Canada Corp

André Denis Leblanc

Jean Thomassin

Eugene Gekht

François Doyon

Charles Faubert

Gilbert Ouellet

A damping system for a gas turbine engine comprises a bearing mounted to a rotor shaft and a support connected to an outer race of the bearing. The support has a wall secured to a casing of the gas turbine engine at a connection portion. The wall has a first surface positioned against a surface of the casing with the first surface being in a non-parallel relation with the rotational axis of the rotor shaft. A cavity is defined in the first surface by a narrowing of a thickness of the wall. The cavity contains a damping fluid to dampen elastic deformation of the wall at the cavity resulting from axial oscillations of the rotor shaft. An abutment is provided to limit an amplitude of the elastic deformation of the wall.

Axial load damping system for rotor shaft

Diffusion in the vane island passages of a centrifugal compressor diffuser is in part controlled by contouring the diffuser passage wall with low profile surface variations. The surface variations can be provided in the form of flow boundary disrupting protrusions disposed within the downstream portion of the vane island passages to prevent flow separation.

Centrifugal compressor vane diffuser wall contouring

An apparatus and method is provided for improving efficiency of a transonic gas turbine engine compressor by bleeding off a shockwave-induced boundary layer from the gas flow passage of the compressor using an array of bleed holes having a downstream edge aligned with a foot of an oblique shock wave which originates on the leading edge of an adjacent transonic rotor blade tip.

Shockwave-induced boundary layer bleed

A radial inlet assembly comprising a radial inlet adapted to be in fluid communication with a compressor, and a restricting member covering the radial inlet and receiving a circumferentially asymmetric airflow, the restricting member partially blocking the airflow around the radial inlet, the restricting member blocking a greater portion of the airflow where the airflow is greater to circumferentially redistribute the airflow in a more symmetric manner in the radial inlet.

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St. Bruno, Canada

André Denis Leblanc