United Technologies Corporation

Raytheon Technologies Corporation

Pw Power Systems, Inc.

Rtx Corporation

Fabian D Betancourt

Jeffrey Leon

Brian J Burke

Kurt Leach

William Indoe

Kimberly Caruso

Fernando K Grant

John J Korzendorfer

Lisa P O'Neill

Amarnath Ramlogan

Charles C Wu

Henry K Webster

Andrew P Boursy

Christopher William Moore

Santiago Orellana

Alexander Sankovich

A turbine rotor for a gas turbine engine includes a disk rotationally disposed about a central axis. The disk includes a bore, a rim and a web disposed radially between the bore and the rim. The bore includes a fore surface including a fore web transition portion, a fore ramp portion radially inward of the fore web transition portion and having a substantially linear portion and a fore base transition portion radially inward of the fore ramp portion. The bore also includes an aft surface including an aft web transition portion, an aft ramp portion radially inward of the aft web transition portion and having a substantially linear portion and an aft base transition portion radially inward of the aft ramp portion. A base portion of the bore includes a spool engagement surface, a first arm extending in an aft direction and a second arm extending in a fore direction and a radially extending first transition portion connecting an aft end of the spool engagement surface to a radially inward portion of the first arm and a radially extending second transition portion connecting a fore end of the spool engagement surface to a radially inward portion of the second arm.

Turbine disk

A turbine rotor for a gas turbine engine includes a disk rotationally disposed about a central axis. The disk includes a bore disposed about the central axis, a rim and a web disposed radially between the bore and the rim. The bore has a fore surface and an aft surface. The aft surface of the bore may include an aft web transition portion, an aft ramp portion radially inward of the aft web transition portion and an aft base transition portion radially inward of the aft ramp portion. The fore surface of the bore may include a fore web transition portion, a fore ramp portion radially inward of the fore web transition portion and a fore base transition portion radially inward of the fore ramp portion. The aft ramp portion includes a substantially linear portion and the fore ramp portion includes a substantially linear portion.

A turbine rotor disk for a gas turbine engine includes a disk rotationally disposed about a central axis. The disk includes a number of blade posts, tabs and slots circumferentially disposed about a rim portion of the disk. The tabs each include a blade post transition portion, a slope portion radially inward of the blade transition portion and a face portion radially inward of the slope portion. The blade posts, tabs and slots are circumferentially oriented about the rim portion such that a tab or slot is positioned radially inward of each blade post.

A turbine rotor disk for a gas turbine engine includes a disk rotationally disposed about a central axis. The disk includes a bore, a rim and a web disposed radially between the bore and the rim. The rim includes a first radially outermost rim portion and a second radially outermost rim portion disposed radially inward of the first radially outermost rim portion. First and second blade posts are disposed proximate the first radially outermost rim portion and spaced circumferentially. First and second tabs are disposed proximate the second radially outermost rim portion and positioned radially inward of the first and second blade posts. A slot is disposed circumferentially between the first tab and the second tab. The first tab and the second tab have an axial profile that includes a blade post transition portion, a slope portion radially inward of the blade transition portion and a face portion radially inward of the slope portion.

A turbine rotor for a gas turbine engine includes a disk rotationally disposed about a central axis. The disk includes an annular bore portion, an annular rim portion and an annular web portion disposed radially between the bore portion and the rim portion. The annular web portion includes an aft surface. A cylindrical arm is disposed on the aft surface and has a first portion extending axially from the aft surface and a second portion extending radially outward from a distal end of the first portion. The intersection of the first portion and the aft surface defines a fillet, radially inward of the first portion. The fillet is defined by a compound radius.

A borescope plug for a gas turbine engine includes a base attachable to a case and defining a base cavity, a shank having a base engagement element at a first end of the shank, and a plug member located at a second end of the shank, the plug member configured to plug a borescope aperture in a borescope vane cluster. The base engagement element fits within the base cavity such that the base moveably retains the base engagement element and wherein the base engagement element can move within the base cavity.

Borescope plug

A gas turbine engine comprises an exhaust section member, a turbine section member, a heat shield and a spacer. The turbine section member is coupled to the exhaust section member. The heat shield is retained between the exhaust section member and the turbine section member. The spacer is positioned between the exhaust section member and the turbine section member to produce a gap for the heat shield. In one embodiment, the exhaust section member comprises a duct and the turbine section member comprises a bearing support.

Spacer for power turbine inlet heat shield

A power turbine section for a gas turbine engine includes a heat shield assembly mounted to a bearing support, the heat shield assembly forms an outer diameter directed toward an inner vane platform of the power turbine vane array.

Power turbine heat shield architecture

A power turbine section for a gas turbine engine includes a heat shield assembly mounted to a bearing support to form a first annular compartment and a second annular compartment.

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Meriden, CT, United States of America

Fabian D Betancourt