Pratt-Whitney Canada Corp

Lorenzo Sanzari

Guy Lefebvre

Panagiota Tsifourdaris

Remy Synnott

John Pietrobon

Franco Di Paola

Krishan Mohan

Othmane Leghzaouni

Masoud Roshan Fekr

Jocelyn Bisson

Francis Gemme

Stephane Bigras

Fariba Ajalli

Sylvain Vignola

Anthony Pham

William Mindenhall

Igal Acher Abenhaim

A compressor assembly has: an impeller rotatable about a central axis, the impeller mounted on a shaft; a bearing housing extending around the central axis and radially supporting the shaft; and a diffuser downstream of the impeller, the diffuser having: an annular member extending circumferentially around the central axis, vanes circumferentially distributed around the central axis and protruding from one of the annular member and the bearing housing, the vanes extending from bases at the one of the annular member and the bearing housing to tips at the other of the annular member and the bearing housing, and lug and slot connections defined between the annular member and the bearing housing to secure the annular member to the bearing housing.

Aircraft engine including diffuser secured to a bearing housing

A bearing assembly for a turbomachine includes a bearing inner race, a bearing outer race located radially outwardly from the bearing inner race, and one or more bearing elements located radially between the bearing inner race and the bearing outer race. A bearing sleeve is positioned radially inboard of the bearing inner race and is configured for engagement with a rotating component. The bearing sleeve includes a sleeve body located radially between the bearing inner race and the rotating component, and a puller feature extending from the sleeve body at a first axial end of the bearing sleeve. The puller feature is configured for application of a removal force thereto to remove the bearing from an installed position in the turbomachine.

Bearing inner race with sleeve and integrated puller

A method of manufacturing an annular bearing housing for a gas turbine engine is provided that includes: producing a flange outer structure segment; producing an intermediate structure segment having an outer radial end, an inner radial end, a body that extends between the outer radial end and the inner radial end, and a branch member that extends outwardly from the body; producing a main body segment; attaching the flange outer structure segment to the outer radial end of the intermediate structure segment; and attaching the main body segment to the inner radial end of the intermediate structure segment. At least one of the flange outer structure segment, the intermediate structure segment, or the main body segment is produced using an additive manufacturing process.

Method of producing a gas turbine engine bearing housing

A rim seal arrangement for a gas turbine engine includes a rotor and a stator. The rotor includes blades circumferentially spaced about a disc hub, each blade including a rotor flange. The stator includes vanes circumferentially spaced and attached to a stationary component, each vane including a stator flange. The stator flange includes an outer surface, an inner surface, a chamfer, and a groove for producing a recirculation flow adjacent to a radial gap between the rotor flange and the stator flange.

Undercut groove and chamfer for rim seal

A turbine blade for a gas turbine engine has an airfoil including leading and trailing edges joined by spaced-apart pressure and suction sides to provide an exterior airfoil surface extending from a platform in a spanwise direction to a tip. The external airfoil surface is formed in substantial conformance with multiple cross-sectional profiles of the airfoil described by a set of Cartesian coordinates set forth in Table 1, the Cartesian coordinates provided by an axial coordinate scaled by a local axial chord, a circumferential coordinate scaled by a local axial chord, and a span location.

Turbine blade airfoil profile

An assembly comprising a blade including a blade portion, a root portion and a platform portion between the blade portion and the root portion, the platform portion defining at least one cavity opened laterally. An abutment projects from a wall portion of the cavity at a trailing end of the blade. A seal is received in the cavity and positioned along a periphery of the cavity, the seal having a trailing edge abutting against the abutment.

Assembly of blade and seal for blade pocket

A rotor disc of a gas turbine rotor assembly is provided. The rotor disc may support a plurality of blades attached thereto. The rotor disc may have a plurality of fixing members defined therein through its peripheral surface and circumferentially spaced apart from one another. The fixing members may extend axially from a front end portion to a rear end portion of the disc. Profiled slots may be defined between pairs of adjacent ones of the fixing members and may be configured to receive complementary profiled blade root portions. A plurality of disc lips may project axially forward from a surrounding surface of the disc in the front end portion. A disc lip may be disposed at a tip portion of a fixing member, adjacent a leading edge of the disc to minimize air leakage at a disc/blade interface. A rotor assembly with such rotor disc and a plurality of blades attached thereto is also provided.

Rotor assembly with rotor disc lip

A rim seal located between a stator and a rotor in a gas turbine engine includes an axial overlap between platform rims of the stator and the rotor. The axial length of the platform rim of one of the stator and the rotor is accommodated within a radially aligned trench defined in the other of the stator and the rotor.

Rim seal

A power turbine includes a first stage blade having an airfoil with a cold un-coated nominal profile substantially in accordance with at least an intermediate portion of the Cartesian coordinate values of X, Y and Z set forth in Table 2. The X and Y values are distances, which when smoothly connected by an appropriate continuing curve, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete airfoil shape.

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Montreal, Canada

Lorenzo Sanzari