General Electric Company

John T Kutney, Jr

Richard William Albrecht, Jr

Robert Harold Weisgerber

Christopher Charles Glynn

Robert J Meade

Daniel G Cameron

Rodger B Mishler

A disk attachment system for a high pressure turbine section of a gas turbine engine, the high pressure turbine section including a first stage disk and a second stage disk. The first stage disk includes a first conical aft shaft extending rearwardly from a bore of the first state disk and the second stage disk has a second conical aft shaft extending rearwardly from a bore of the second stage disk, and the second aft shaft is attached to the first aft shaft at a splined connection. The second aft shaft includes an arm having a mate face and pilot for centering the second stage disk relative to the first stage disk. Rotational energy from the second stage disk is transmitted through the first aft shaft to the first stage disk.

Turbine disk attachment system

A forward seal assembly located in a turbine section of a turbine engine, the turbine section having a disk including a web, a bore, and a forward shaft integral with the web, wherein the forward seal assembly includes a face plate extending from the forward shaft to an outer periphery of the disk and includes orifices for conveying cooling air to the web. The face plate includes a plurality of radially inwardly-extending tabs shaped to engage radially outwardly-extending tabs located on the web to form a bayonet connection. The forward seal assembly further includes radially extending vanes to convey cooling air along the disk, and is secured by inward and outward bayonet connections, the inward connection including locking pins which are arranged to perform a balanced function.

Turbine disk forward seal assembly

A turbine engine of the type having a compressor section, combustor section and high-pressure turbine section in which compressor air is conveyed internally of the compressor and turbine sections to cool the turbine interstage volume, a first stage turbine disk includes a shaft supporting a second stage turbine disk, a turbine interstage seal is secured by boltless engagement to the disks and is prestressed to resist flexure, and the first stage disk carries a forward seal attached by boltless connections. The interstage seal includes a bore having a rearwardly-extending arm engaging the aft shaft in a bayonet connection to prevent deflection of the bore and includes passages to allow air flow around the bore. The forward seal includes radially-extending vanes to convey cooling air along the disk, and is secured by inward and outward bayonet connections, the inward connection including locking pins which are arranged to perform a balancing function.

Turbine disk interstage seal system

A drag-reducing structure is provided on a pylon that suspends a wing-mounted engine. The structure reduces drag by preventing ambient airflow, in a region between the wing, pylon, and engine, from accelerating to supersonic velocities and causing shock waves resulting in excessive drag. In one embodiment, the structure is a broad fairing on the inboard vertical surface of the pylon. In another embodiment, the structure is a tapered bump mounted at the inboard intersection between the wing and pylon.

Drag-reducing component

An inlet duct for use with gas turbine engines or the like is provided with an axially upstream projecting deflector means to reduce noise propagation emanating within said duct. The deflector member has an essentially double arcuate contour of the lip in the axial direction which improves noise attenuation and inlet total pressure recovery. The contour is provided with at least one point of curvature inflection.

Growing community of inventors

Cincinnati, OH, United States of America

John T Kutney, Jr