United Technologies Corporation

Raytheon Technologies Corporation

Pw Power Systems, Inc.

Andrew P Boursy

Peter E Gunderson

James W Taubler

Sunny Anant Patel

John J Korzendorfer

Ky H Vu

Lisa P O'Neill

Fabian D Betancourt

Charles C Wu

Takao Fukuda

Henry K Webster

Fernando K Grant

Christopher William Moore

Andy Turko

Gerald M Mace

Lynn M Boy

Alexander Sankovich

Lnyy M Boy

Gerald M Mace Jr

An engine component for a gas turbine engine may include a radial channel and an axial channel disposed in the engine component. The radial channel may be configured to direct a cooling air in a radial direction. The axial channel may be configured to direct the cooling air in a direction substantially perpendicular to the radial direction. A cross-section area of the axial channel is greater than a cross-section area of the radial channel, such that the radial channel remains the metering channel, independent of the relative location due to radial movement of the engine component with respect to an adjacent engine component.

Radial-axial cooling slots

An air seal may comprise an annular ring defined by at least a proximal surface, a distal surface, an aft side and a forward side. A channel may be disposed in the forward side of the air seal and/or the aft side of the air seal and may extend between the proximal surface and the distal surface. An additional channel extending from at least one of the forward side or the aft side may be disposed in the distal surface. The channel and the additional channel may be circumferentially in line. The channels may define a flow path for direction cooling air from a proximal side of the air seal to a distal side of the air seal. The radial channel may interface with the axial channel at an edge of the air seal.

Axial-radial cooling slots on inner air seal

An air seal may comprise an annular ring defined by at least a proximal surface, a distal surface, an aft side and a forward side. A channel may be disposed in the forward side of the air seal and/or the aft side of the air seal and may extend between the proximal surface and the distal surface. An additional channel extending from at least one of the forward side or the aft side may be disposed in the distal surface. The channel and the additional channel may be circumferentially in line. The channels may define a flow path for direction cooling air from a proximal side of the air seal to a distal side of the air seal.

An airfoil component for a gas turbine engine includes a platform. The airfoil component includes a flow path surface from which an airfoil extends. A laterally extending aft surface is adjacent to the flow path surface. A contoured surface adjoins the flow path surface and the aft surface. An airfoil component for a gas turbine engine includes a platform. The airfoil component includes a flow path surface from which an airfoil extends. A laterally extending aft surface is adjacent to the flow path surface. A contoured surface adjoins the flow path surface and the aft surface. The aft surface extends from a first aft edge to a second aft edge at a circumferentially extending edge. The contoured surface is arranged inboard from at least one of the first and second edges.

Gas turbine engine airfoil platform edge geometry

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 turbine (18) of a gas turbine engine includes erosion energy dissipaters (44) which comprise of a plurality of inlet orifices (46) and a large diameter outlet orifice (48). The erosion energy dissipater reduces erosion of associated structure due to impingement of particulates entrained in airstreams. Various construction details are described to provide cooling air containing entrained particulates to the high pressure turbine case of a gas turbine engine without eroding the case.

Erosion energy dissipater

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Marlborough, CT, United States of America

Andrew P Boursy