United Technologies Corporation

Raytheon Technologies Corporation

Other

Rtx Corporation

James R Midgley

David P Houston

Timothy B Winfield

Frederick M Schwarz

Timothy Dale

Paul J Hiester

David M Nissley

Marnie A Rizo

Madeline Campbell

Richard P Meisner

Eric W Malmborg

Jonathan Lemoine

David Lei Ma

Joseph W Bridges, Jr

Robert A Grelotti

Michael J Schober

Madeline N Campbell

A full authority digital engine controller (FADEC) based system is also disclosed. The system includes a processor, and a tangible, non-transitory memory configured to communicate with the processor, the tangible, non-transitory memory having instructions stored thereon that, in response to execution by the processor, cause the FADEC to perform operations. The operations may include measuring a first temperature at a first sensor disposed at a first known location of an engine, measuring a second temperature at a second sensor disposed at a second known location of the engine, and estimating at least one of a stress or a strain of a part or component in the engine based on the first temperature and the second temperature. The system may control fuel flow and/or other engine effectors during a thrust transient to limit the estimated stress or the estimated strain of the component from exceeding a predetermined threshold.

Transient control to extend part life in gas turbine engine

A method of monitoring a gas turbine engine includes the steps of: (a) receiving information from actual flights of an aircraft including an engine to be monitored, and including at least one of the ambient temperature at takeoff, and internal engine pressures, temperatures and speeds; (b) evaluating the damage accumulated on an engine component given the data received in step (a); (c) storing the determined damage from step (b); (d) repeating steps (a)-(c); (e) recommending a suggested future use for the component based upon steps (a)-(d). A system is also disclosed.

Gas turbine engine with lifing calculations based upon actual usage

A rotor stack assembly for a gas turbine engine includes a first rotor assembly and a second rotor assembly axially downstream from the first rotor assembly. The first rotor assembly and the second rotor assembly include a rim, a bore and a web that extends between the rim and the bore. A tie shaft is positioned radially inward of the bores. The tie shaft maintains a compressive load on the first rotor assembly and the second rotor assembly. The compressive load is communicated through a first load path of the first rotor assembly and a second load path of the second rotor assembly. At least one of the first load path and the second load path is radially inboard of the rims.

Gas turbine engine rotor stack assembly

A gun handling deterrent device includes a housed, battery-powered electrical assembly for placement within the gun handle, with sub-assemblies to convert the DC to pulsating DC and step up the voltage, and leads to the gun frame and a negative contact member that extends from the handle for positioning adjacent the handle, trigger guard and barrel, such that when the handle, trigger guard or barrel is grasped, the hand contacts both the metal frame and the negative contact member. An actuator switch enables the circuit when the gun is moved from a horizontal position, causing the increased voltage pulsating DC to be delivered to the hand. The shock function is joined or replaced in embodiments where an audio generating device is activated by the actuator switch when the gun is so moved.

Behavior modification device for handguns

Growing community of inventors

Cromwell, CT, United States of America

James R Midgley