Honeywell International Inc.

Alan Tiltman

Mark C Morris

Kin Poon

Larry K Ball

Jeff Howe

Peter Hall

Alexander MirzaMoghadam

William J Howe

Dave Dischinger

George E Zurmehly

Bradley Volkmann

Victor Reyes

Mike O'Brien

George W Wolfmeyer

Rich Barrett

Khosro Molla Hosseini

Douglas Spencer

Daniel Troller

James Ebken

Tina H Chaney

Dwight D Vettel

John F Sciacca

Coleen Anne Cramer

Don Rossi

A stator attachment system couples a stator to a compressor case that is split to define a first half and a second half. The stator attachment system includes a plurality of retention slots defined in each of the first half and the second half of the compressor case. The plurality of retention slots is spaced apart about a perimeter of the first half and the second half such that at least one of the plurality of retention slots associated with the first half is vertically aligned with at least one of the plurality of retention slots associated with the second half. The stator attachment system includes a plurality of tabs defined on the stator that extend radially outward from the stator. Each of the plurality of tabs is configured to engage with one of the plurality of retention slots to couple the stator to the compressor case.

Stator attachment system for gas turbine engine

An impeller or axial stage compressor disk backface shroud for use with a gas turbine engine is disclosed. The backface shroud includes, but is not limited to, a substantially funnel shaped body having a surface. The substantially funnel shaped body is configured to be statically mounted to the gas turbine engine substantially coaxially with the impeller or axial stage compressor disk. The surface and a backface of the impeller or axial stage compressor disk form a cavity that guides an airflow portion to a turbine when the substantially funnel shaped body is mounted coaxially with the impeller or axial stage compressor disk and axially spaced apart therefrom. The airflow portion has a tangential velocity and a recessed groove in the surface of the backface shroud is oriented generally transversely to the tangential velocity to at least partially interfere with the airflow portion, thus affecting static pressure in the cavity.

Impeller backface shroud for use with a gas turbine engine

A lubrication system is provided for delivering a lubricant to a plurality of nozzles. The lubrication system includes a reservoir for the lubricant; a pump fluidly coupled to the reservoir and configured to remove a flow of the lubricant from the reservoir; a lubrication sensor positioned between the pump and the plurality of nozzles and configured to detect a blockage in the plurality of nozzles and to generate a blockage signal when the blockage is detected; and an indicator coupled to the lubrication sensor and configured to generate a warning based on the blockage signal from the lubrication sensor.

Lubrication systems with nozzle blockage detection systems

An anti-ice formation device for a gas turbine engine is configured to be mounted within an inlet duct of the engine, and adjacent the gas turbine engine compressor inlet. The device is configured to selectively receive a flow of compressed air that is discharged from the compressor. Because the compressed air is relatively hot, the anti-ice formation device temperature increases to a temperature sufficient to prevent ice accumulation and formation in the engine inlet duct. The anti-ice formation device is also configured such that heat is not transferred to the compressor inlet housing. As a result, the anti-ice formation device does not cause impeller clearance variations, which would adversely affect engine performance.

Gas turbine engine anti-ice formation device and system

A gas turbine engine is configured to use relatively cool, low pressure air discharged from a low pressure compressor to supply buffer air to lubrication sump seals. The engine is further configured such that the lubrication sump is thermally layered by isolating relatively hot, high pressure compressor air from the sump by utilizing a warm vent mixing cavity, which is located radially between of the hot high pressure compressor air and the cool buffer air, which is located in a buffer cavity between the vent cavity and the sump.

Gas turbine engine including a low pressure sump seal buffer source and thermally isolated sump

A cooled shroud assembly includes an angled slot and a plurality of dilution jet openings. The shroud forward cavity is modified such that at least one recirculation zone is produced. The angled slot forces an axial change in momentum of the hot gas flow and increases radial and axial pressure variation attenuation. The cooled shroud assembly isolates the shroud structure and seals from the hot flow path and a cooling flow from the dilution jet openings dilutes the hot gas flow. A series of recirculation zones shields the shroud carrier and high pressure seals from the hot gas flow.

Gas turbine cooled shroud assembly with hot gas ingestion suppression

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Fountain Hills, AZ, United States of America

Alan Tiltman