General Electric Company

John Lawrence Noon

John Alan Manteiga

Jeffrey Howard Nussbaum

Robert John Parks

Mark Michael D'Andrea

Marcus Joseph Ottaviano

Thomas Michael Regan

Joseph Capozzi

Aaron Todd Williams

A gas turbine engine centrifugal compressor axial forward thrust apparatus bleeds impeller tip aft bleed flow from between an annular centrifugal compressor impeller of a high pressure rotor and a diffuser directly downstream of the impeller. The apparatus then uses the aft bleed flow to pressurize an annular cavity extending radially between an inner combustor casing and the rotor and extending axially between forward and aft thrust balance seals. Forward and aft thrust balance lands are in sealing engagement with the forward and aft thrust balance seals on the high pressure rotor respectively. An annular stator plenum in fluid communication with the annular cavity is bounded in part by a forward end wall having conical diffusion holes therethrough which may be axially or circumferentially or axially and circumferentially angled. The forward thrust balance seal may be on an aft conical arm of the impeller.

Centrifugal compressor forward thrust and turbine cooling apparatus

A gas turbine engine turbine cooling system includes an impeller and a diffuser directly downstream of the impeller, a bleed for bleeding clean cooling air from downstream of the diffuser, and one or more channels in fluid communication with the bleed. Each of the channels having a generally radially extending section followed by a generally axially aftwardly extending section terminating at an annular cooling air plenum connected to accelerators. The radially and axially aftwardly extending sections may be connected by a bend section of the cooling air channel and the axially aftwardly extending section may be angled radially inwardly going from the bend section to the cooling air plenum. Each of the cooling channels includes an inner wall formed by a forward end wall extending radially outwardly from an inner combustor casing, an annular cover covering a radially inner portion of the forward end wall, and the inner combustor casing.

Turbine cooling air from a centrifugal compressor

A fan outlet guide vane includes integral outer and inner platforms conforming to arcuate sides thereof, and multiple mounting bosses on the platforms. The platform sides are arcuate to conform with the vane sides for improving aerodynamic efficiency. The multiple mounting bosses improve mounting of the vanes to corresponding supporting rings.

Conforming platform guide vane

A stator vane frame assembly including an outer structure ring, an inner structure ring, a set of discrete vanes each connecting the outer structure ring and the inner structure ring forming an inner and outer platforms with neighboring vanes defining a set of flow paths, a set of sealing members contoured to a set of gaps between the set of vanes disposed to sealing the gap. A method for applying a sealing member to the gaps between a platform formed resulting from the coupling between vanes including affixing a set of stator vanes on an inner frame and an outer frame, and sealing a set of sealing members on the backside surface of a stator vane frame. The discrete nature of individual vane blade sealed by the sealing members renders the stator vane frame assembly to add a damping effect which increases the fatigue life of the vane, and permits the use of lower strength, lighter, and less expensive material.

Growing community of inventors

Swampscott, MA, United States of America

John Lawrence Noon