Honeywell International Inc.

Mark Knowles

Shawn Alstad

Danis Burton Smith

Robert Romano

David Robinson

Justin C Mickelsen

Morris G Anderson

John Taylor Pearson

Raymond Gage

Bill Russell Watson

Laurence David Noble Liston

A thrust reverser system comprising a single row vane assembly is provided. The provided thrust reverser system is capable of meeting performance requirements for turbine engines with reduced weight and cost.

Single row vane assembly for a thrust reverser

A thrust reverser system for a turbine engine includes a support structure, a transcowl, a door, and an anti-rotation structure. The transcowl is mounted on the support structure and has an inner surface. The transcowl is axially translatable, relative to the support structure, between first and second positions. The door is pivotally coupled to the turbine engine, and has a forward edge and an aft edge. The door is rotatable between stowed and deployed positions when the transcowl translates between the first and second positions, respectively. The anti-rotation structure extends from the transcowl and is disposed adjacent to the aft edge of the door when the transcowl is in the first position and the door is in the stowed position. The anti-rotation structure is configured such that door rotation out of the stowed position only occurs subsequent to or concurrently with translation of the transcowl out of the first position.

Translating cowl thrust reverser that prevents unintended door rotation

A system and method for reducing idle thrust in a translating cowl reverser system is provided. The provided system and method provide a partial deployment, or thrust reverser system intermediate position for a translating cowl thrust reverser system.

System and method for reducing idle thrust in a translating cowl thrust reverser

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 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.

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Mesa, AZ, United States of America

Mark Knowles