Honeywell International Inc.

Justin C Mickelsen

Shawn Alstad

Martin Carlin Baker

Mark Knowles

Mark C Morris

Donald G Godfrey

Morris G Anderson

David R Waldman

Robert Romano

Brian G Baughman

Raymond Gage

Dave Dischinger

Patrick S Mulloy

Mark McNair

Bill Russell Watson

Alexandre Guerinot

Jeff Guymon

Aaron Duncan

Laurence David Noble Liston

Jeffrey T Peters

Matthew D Greenman

Mark Mcnair

A thrust reverser system for a gas turbine engine includes at least one hinge coupled to the thrust reverser system so as to be adjacent to at least one opening defined in the thrust reverser system. The thrust reverser system includes at least one body coupled to the at least one hinge. The at least one body has a first body end and an opposing second body end. The body pivotally coupled to the hinge such that a portion of the body is positionable within the at least one opening and the body includes at least one counterweight at the first body end or the second body end. The body is positioned within the at least one opening based on an operating condition of the gas turbine engine.

Systems and methods for thrust reverser with temperature and fluid management

A mount system provides vibration isolation and support through a hybrid hard-soft configuration. The mount system includes a frame and a body connected with the frame. A first coupling element is provided on the body and defines a first opening. A second coupling element is provided on the frame and defines a second opening. A pin extends through the first and second openings to couple the body to the frame. At least one of the first and/or second openings operates as a damping hole with a series of slits disposed about the damping hole, so that the damping hole with the slits is configured to deflect to reduce the transmission of vibrations between the body and the frame.

Hybrid motion mount system

A thrust reverser system for a gas turbine engine includes a transcowl movable between a stowed position, a deployed position and a partially deployed position between the stowed position and the deployed position by at least one actuator. The system includes a temperature sensor and at least one resistance sensor. The thrust reverser system includes a controller, having a processor, that: outputs one or more control signals to move the transcowl to the partially deployed position; determines whether a temperature associated with the transcowl exceeds a temperature threshold; outputs one or more control signals to move the transcowl from the partially deployed position to the stowed position; determines whether the transcowl has encountered resistance; and based on the determination, outputs one or more control signals to stop a movement of the transcowl and outputs the one or more control signals to move the transcowl to the partially deployed position.

A heat resistant washer for a heat resistant fastening system and a heat resistant fastening system is provided. The heat resistant washer includes a fire retardant material, and a housing that includes a base and a flange, with a throughbore defined through the base to receive a fastener. The housing defines a cavity adjacent to the throughbore and at least one guide. The fire retardant material is disposed within the cavity and the at least one guide directs the fire retardant material in an active state out of the cavity.

Heat resistant fastening systems

A system and method is provided that combines fan bypass components and minimizes assembly interfaces in a turbofan engine. The system and method provide a front frame structure of reduced weight that slidably installs/removes from within the combined fan bypass components.

Combined fan bypass components with removable front frame structure for use in a turbofan engine and method for making same

A coupling apparatus for use in sealingly connecting a first fluid flow path to a second fluid flow path. The coupling apparatus includes a rigid fluid flow channel having a first end and a second end, wherein the fluid flow channel is substantially rigid in an axial direction and a radial direction, a first sealing terminus that is rigidly connected to the first end and that is configured for sealing with the first fluid flow path, and a second sealing terminus that is slidingly disposed about the second end such that the second sealing terminus is configured for relative movement with respect to the second end, and wherein the second sealing terminus is further configured for sealing with the second fluid flow path. The coupling apparatus further includes a flexible coupler connected to both the first sealing terminus and the second sealing terminus and surrounding the fluid flow channel, wherein the coupler is relatively more flexible in the axial direction and the radial direction as compared to the fluid flow channel.

Turbine engine couplings and methods for manufacturing turbine engine couplings

A system and method is provided for an integrated aircraft turbofan engine outer flowpath ducting and front frame that minimizes assembly interfaces and reduces overall aircraft engine weight. The system and method provide an integrated turbofan engine outer flowpath ducting and front frame system that decouples the fairing/aerodynamic duties from the struts/weight bearing duties thereby enabling efficient distribution of mechanical load.

Integrated outer flowpath ducting and front frame system for use in a turbofan engine and method for making same

A local fire shield is provided for protecting an attachment point of a fireproof system in an engine during a fire event. The local fire shield includes a mounting plate mounted on the attachment point; and a cover coupled to the mounting plate for covering the attachment point during the fire event.

Fireproof systems with local heat shields for aircraft engines

Apparatuses are provided for reducing noise generation from a dead ended conduit in a gas turbine engine. In particular A scooped bellmouth is provided that comprises a bellmouth within a surface having an outer perimeter an inner perimeter and a ramp diverging from the surface at a first end, the ramp extending radially through the outer perimeter of the bellmouth at a second end. The ramp diverts an airflow away from the bellmouth thereby preventing the development of a low pressure area at the bellmouth without affecting the efficiency of the gas turbine engine.

Turbine engine bypass fan-bleed noise reduction

A fireproof system is provided for protecting a structure during a fire event. The system includes a fire resistant panel defining a first attachment opening and disposed adjacent to the structure; a canister including a side wall defining a first end and a second end, and an end wall enclosing the first end and defining a second attachment opening that is aligned with the first attachment opening; a fastener extending through the canister at the second attachment opening and the fire resistant panel at the first attachment opening such that the canister, the fire resistant panel, and the structure are fastened together; and a fire retardant agent disposed within the canister in an inactive condition and configured to transition out of the second end of the canister in an active condition at a predetermined temperature.

Growing community of inventors

Phoenix, AZ, United States of America

Justin C Mickelsen