Hamilton Sundstrand Corporation

United Technologies Corporation

Sundstrand Corporation

Eric J Alexander

Anthony C Jones

Gordon F Jewess

Patrick M Lydon

Mark M Harris

Walter Ainslie

David Ronald Adair

Robert O Barkley

Behzad Hagshenas

James C Napier

Brian C DeDe

David Lau

Nagamany Thayalakhandan

Richard L Elgin

David Eugene Martinez

Mark N Shatz

Tammy L Lane

James J McLaughlin

Robert W Fawley

Mark N Shatz′

Buzz Hagshenas

Davis Bunone

Charles Brian Travelbee

A gas turbine engine has a nose cone with a nose cone upstream end and an inlet housing including a plurality of separate flow paths at a housing upstream end which is downstream of the nose cone upstream end. The inlet housing includes a mixing portion downstream of the housing upstream end which mixes airflow from the separate flow paths, such that the airflow is generally around 360 degrees of a rotational axis of the gas turbine engine. A rotor and a turbine drive a shaft to drive the rotor with the shaft including a bearing mounted at a location downstream of the nose cone upstream end.

Bifurcated air inlet housing for a miniature gas turbine engine

The present disclosure is applicable to all vehicles having an engine mounted therein. In one embodiment, an aft mount system for a gas turbine engine is disclosed. The aft mount system includes a vehicle chassis and at least one flexible mounting member disposed within the vehicle chassis, wherein when a gas turbine engine is received within the vehicle chassis, an exhaust portion of the gas turbine engine is substantially mounted within the vehicle chassis through engagement with the at least one flexible mounting member.

System and method for aft mount of gas turbine engine

A nozzle formed of one piece for a jet engine includes a mixing tube, a fuel conduit integrally formed with the mixing tube, and an opening through the fuel conduit and directed radially into the mixing tube.

One-piece fuel nozzle for a thrust engine

An example method of sealing an interface within a gas turbine engine includes holding a sealing ring arrangement relative to a turbine nozzle using a flange extending from a combustor liner. The method further includes urging the sealing ring arrangement toward a sealed relationship with the turbine nozzle.

Method of sealing combustor liner and turbine nozzle interface

A catcher for a gas turbine engine includes a central hub, a plurality of struts, and a first ring. The plurality of struts are connected to and extend outward from the central hub. The first ring is connected to a mid-section of the plurality of struts and extends therebetween.

Turbine wheel catcher

A system for reducing moisture in a gas turbine engine with one or more air ducts includes one or more one or more covers, each with an outer face and an inner face, with the inner face connectable to the air duct, wherein the cover is shaped to engage and close the air duct and a desiccant that is attachable to the cover.

Apparatus and method for preventing gas turbine engine freezing

A removable stand assembly for a gas turbine engine includes a first stand removably mountable to a gas turbine engine on one side of a center of gravity of the gas turbine engine and a second stand removably mountable to the gas turbine engine on a second side of the center of gravity of the gas turbine engine.

Removable gas turbine engine stand

A rotational system for a miniature gas turbine engine includes a rotor shaft rotationally mounted to a forward bearing and an aft bearing. The rotor shaft is located axially with a single threaded rotor nut which provides an axial preload maintained by a fixed compressor wheel and spacers. A preload spring provides dynamic compensation for tolerance variation and undesirable axial movement during rotation of the shaft. A permanent magnet generator is mounted to the rotor shaft behind the forward bearing to generate electrical power for the engine and other accessories. The rotor shaft is inertia welded to a turbine wheel to form a cavity which provides a thermally conductive path away from the aft bearing. A seal ring mounted within a groove within the rotor shaft provides a pneumatic seal to further protect the aft bearing from thermal transfer between the turbine section and the compressor section.

Rotational system for an expendable gas turbine engine

A thermal management system and method for a miniature gas turbine engine includes a forward cover having a filter portion along an axis of rotation of a gas turbine engine, a first lubrication passage and a second lubrication passage.

Thermal management system for a gas turbine engine

A gas turbine engine sealing arrangement which includes a combustor liner establishing a combustion area and a turbine nozzle configured to receive a portion of a combustor liner. A sealing ring arrangement is configured to seal with the turbine nozzle to control fluid flow from the combustion area and reduce leakage.

Combustor interface sealing arrangement

A rotary bearing system that supports a shaft for rotating machinery in a housing comprises: at least one stationary rotary bearing mounted in the housing for supporting a respective journal of the shaft in a desired axial and radial alignment; at least one slidable rotary bearing, with an outer surface mounted within a respective inner support surface of the housing to form a respective linear bearing such that each slidable bearing may slide axially along the inner support surface of the housing, for supporting another respective journal of the shaft with the desired radial alignment; and at least one layer of a crystalline material that exhibits a high degree of basal cleavage bonded to at least one of the linear bearing surfaces; wherein each layer of crystalline material allows each slidable rotary bearing to slide axially along each respective linear bearing to compensate for differences in the coefficient of expansion of the housing and the shaft so as to prevent the bearing system from binding due to extreme environmental conditions.

High speed bearing system with bind-free axial displacement

A fuel delivery system for a gas turbine engine that delivers fuel to a combustor of the engine and lubricates bearings of the engine with fuel, comprising: a tank for storing the fuel; a pump for delivering a continuous flow of fuel from the tank to the combustor by way of a combustor inlet stream and the engine bearings by way of a bearing lubrication stream; a pressurized container for storing fuel lubrication additive under pressure; and a flow valve for controlling flow of fuel lubrication additive that flows from the pressurized container into the bearing lubrication inlet stream to mix with the fuel delivered to the engine bearings.

Engine with fuel/lubricant supply system for bearing lubrication

A thermal management system for a gas turbine engine includes a cooling airflow which enters through an air filter portion of a forward cover for filtration of particulate which may result in FOD to a rotational system of the engine. Filtered cooling airflow flows along a rotor shaft over and through a forward bearing, over and through a permanent magnet generator, then over and through an aft bearing to provide thermal management. Commensurate therewith, the cooling airflow atomizes and communicates a lubricant to the bearings. From the aft bearing, the cooling airflow merges with a primary airflow path from an intake which generally surrounds the forward cover.

A static structure for a miniature gas turbine engine includes a forward housing, a forward cover, a diffuser housing, a diffuser, a turbine nozzle, a combustor liner, a combustor housing and an exhaust pipe with relatively uncomplicated assembly interfaces. The static structure defines airflow and lubrication passages which communicate lubricant and airflow to each shaft bearing such that an adequate measured quantity of lubricant is supplied to the bearings in response to engine speed. The airflow through the airflow passage carries the lubrication supplied to the forward bearing toward the aft bearing to further lubricate the aft hot section bearing.

Static structure for an expendable gas turbine engine

A turbofan engine includes a combined stage rotor mounted for common rotation with a shaft, a compressor stage, and a turbine stage. Each of the plurality of fan blades of the combined stage rotor are contiguous with a respective compressor blade. The combined stage rotor is located at a junction between a fan bypass duct and a core duct. The fan bypass stage portion includes a plurality of the fan blades which communicate incoming airflow into fan bypass airflow through the fan bypass duct. The compressor stage portion includes a plurality of the compressor blades which communicated airflow into core airflow through the core duct. The plurality of fan blades extend substantially perpendicular to the plurality of compressor blades such that the plurality of compressor blade portions extend at least partially into the core duct and preferably will include splitters for enhanced efficiency.

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San Diego, CA, United States of America

Eric J Alexander