General Electric Company

Glen William Royal

Christopher Charles Glynn

Robert Proctor

Julius John Montgomery

Nathan Gerard Cormier

Stephen Craig Mitchell

Michael J Epstein

Robert Joseph Albers

Richard William Jendrix

Zhifeng Dong

Jay Alan Benson

Massimo Rufo

Samir Dimitri Sayegh

An enclosure for apparatus that, during operation, generates heat and/or sound energy comprises at least one wall defining at least a portion of the enclosure hollow interior. The wall comprises in sequence outwardly from the enclosure hollow interior an inner panel, an outer panel, a support frame between the inner and outer panels to hold the inner and outer panels spaced apart, and a vibrator isolator between the support frame and the panels. Panels or panel segments of the wall primarily are made of non-metallic composites to provide a structurally strong, lightweight enclosure that includes enhanced acoustic characteristics and reduced heat transfer through enclosure walls, along with fire protection and in-plane shear loading capabilities.

Thermal&#x2014;acoustic enclosure

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 enables a gas turbine engine to be assembled. The method comprises coupling a rotor assembly including a plurality of circumferentially-spaced rotor blades downstream from, and in flow communication with, a compressor, coupling a casing assembly circumferentially around the rotor assembly such that a clearance is defined between an inner shroud surface of the casing assembly and the rotor blade tips, and coupling a clearance control system to the casing assembly to facilitate maintaining the clearance between the casing assembly and the rotor blade tips, wherein at least a portion of an external surface of the clearance control system is formed with a textured pattern that facilitates increasing the clearance control closure capability during engine operation.

Methods and apparatus for maintaining rotor assembly tip clearances

An impingement baffle includes a perforate plate having a pattern of impingement holes. An imperforate deflector is spaced from the plate and is smaller than the plate for deflecting inlet air around the deflector to the holes. The baffle is disposed between a turbine shroud and supporting hanger, and the deflector is disposed between the hanger and the baffle.

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Cincinnati, OH, United States of America

Glen William Royal