General Electric Company

Other

Nathan Gerard Cormier

Christopher Charles Glynn

Robert Proctor

James Edwin Rhoda

Julius John Montgomery

Glen William Royal

Richard William Jendrix

Wayne Ray Bowen

Mitchell Jay Headley

Glenn B Sinclair

Steven Roy Manwaring

A method of assembling a gas turbine engine includes providing a gas turbine engine including a compressor, a combustor downstream from the compressor, and a turbine coupled to the compressor, and coupling a seal assembly aft of the compressor such that air discharged through the seal assembly facilitates reducing the cavity pressure, and therefore reducing the axial forces induced to an aft side of the compressor.

Gas turbine engines seal assembly and methods of assembling the same

A method of manufacturing a gas turbine engine includes providing a turbine mid-frame, coupling a plurality of rotor blades to a rotor disk, the rotor disk is coupled axially aft from the turbine mid-frame such that a cavity is defined between the rotor disk and the turbine mid-frame, and forming at least one opening extending through the turbine mid-frame to facilitate channeling cooling air into the gap, the opening configured to impart a high relative tangential velocity into the cooling air discharged from the opening.

Methods and apparatuses for cooling gas turbine engine rotor assemblies

A method facilitates assembling a variable vane assembly for a gas turbine engine including a casing and an inner shroud. The method comprises providing at least one variable vane including a radially inner spindle that includes a groove defined therein that has at least one machined face, and coupling the variable vane radially between the casing and the inner shroud such that at least a portion of the radially inner spindle is inserted at least partially through an opening extending radially through the inner shroud. The method also comprises securing the variable vane to the inner shroud by engaging the spindle machined face with a retainer coupled to the inner shroud.

Gas turbine engine variable vane assembly

A method of assembling a gas turbine engine includes providing a plurality of stator vane sectors that each include an equal number of stator vanes that are circumferentially-spaced such that a first circumferential spacing is defined between each pair of adjacent stator vanes within the sector, and coupling the plurality of stator vane sectors together to form a stator vane assembly such that a second circumferential spacing is defined between each pair of adjacent stator vanes coupled to adjacent sectors, wherein the second circumferential spacing is different from the first circumferential spacing.

Methods and apparatus for assembling gas turbine engines

An improved gas turbine engine, a blade for a gas turbine for attachment to a rotor disk of the gas turbine engine and a method for manufacturing thereof. Specifically, the blade includes an airfoil attached to at least one base, wherein each of the bases is adapted to be received within a slot defined in the disk. At least one of the bases has a contacting surface for contacting a corresponding surface of the disk. At least one of the contacting surfaces is crowned.

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Cincinnati, OH, United States of America

Nathan Gerard Cormier