General Electric Company

Wilhelm Ramon Hernandez

John Alan Manteiga

David Vickery Parker

Paul Trimby

Basuki Srivastava

Patrick Murphy

Victor Hugo Silva Correia

Daniel Edward Demers

Tyler Frederick Hooper

Robert John Parks

Thet Kwan

Troy Todd Dennis

An example compressor includes a casing having a main portion and an outer skirt collectively defining an annular plenum, an outlet guide vane coupled to the main portion, an actuator mounted outside the outer skirt, and a linkage coupled to the actuator and the outlet guide vane through the annular plenum.

Axi-centrifugal compressor with variable outlet guide vanes

A compressor apparatus includes: an upstream portion comprising an axial-flow compressor; a downstream portion comprising a centrifugal-flow compressor; and a row of variable-stagger-angle outlet guide vanes disposed between the upstream and downstream portions.

An apparatus and method of cooling a hot portion of a gas turbine engine, such as a rotor disk, by having a vane assembly with a cooling air passage and a flow control insert located within the cooling air passage defining a conduit. A turning nozzle is mounted to the vane and has a turning passage with an inlet and an outlet, the turning nozzle is fluidly coupled to the flow control insert outlet.

Gas turbine engine with a vane having a cooling air turning nozzle

A turbine frame assembly for a gas turbine engine includes: (a) a turbine frame including: (i) an outer ring; (ii) a hub; (ii) a plurality of struts extending between the hub and the outer ring; (b) a two-piece strut fairing surrounding each of the struts, including: (i) an inner band; (ii) an outer band; and (iii) an airfoil-shaped vane extending between the inner and outer bands; (d) a plurality of nozzle segments disposed between the outer ring and the hub, each nozzle segment being an integral metallic casting including: (i) an arcuate outer band; (ii) an arcuate inner band; and (ii) an airfoil-shaped vane.

Turbine frame assembly and method for a gas turbine engine

A fairing for a structural strut in a gas turbine engine includes: (a) an inner band; (b) an outer band; (c) a hollow, airfoil-shaped vane extending between the inner and outer bands; (d) wherein the fairing is split along a generally transverse plane passing through the inner band, outer band and vane, so as to define a nose piece and a tail piece; and (e) complementary structures carried by the nose piece and the tail piece adapted to secure the nose piece and the tail piece to each other.

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Lynn, MA, United States of America

Wilhelm Ramon Hernandez