Honeywell International Inc.

Robert Romano

Danis Burton Smith

Shawn Alstad

Morris G Anderson

Mark Knowles

David Robinson

Kevin K Chakkera

Robert G Hoover

Justin C Mickelsen

John Taylor Pearson

Paul W Banta

Don Weir

Jeff M Mendoza

Dan Judd

Matthew D Greenman

Jeffrey T Peters

James W Brackin

David W Zmora

A thrust reverser system for a turbine engine includes a support structure, a transcowl, a door, a lock, and a first elastic element. The transcowl is mounted on the support structure and is translatable between a stowed position, a deployed position, and an over-stow position. The door is pivotally coupled to the support structure and is rotatable between at least a first position, a second position, and a third position. The lock is movable between a locked position, to prevent transcowl translation toward the deployed position, and an unlocked position, to allow transcowl translation toward the deployed position. The lock is only able to move to the unlocked position when the transcowl is in the over-stow position. The first elastic element is disposed within the stowed position aperture and, when engaging both the support structure and the transcowl, supplies a force to the transcowl.

Translating cowl thrust reverser system with over-stow unlocking capability

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 for monitoring a thrust reverser system are provided. The embodiments described herein utilize sensors located proximate locks comprising a thrust reverser locking system. The provided system and method detect deflection and displacement proximate the locks to determine when individual locks have failed.

System and method for monitoring a translating cowl thrust reverser

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 bleed air duct that preferably includes an inlet section configured to include a flush scoop and a louver. The louver is located and configured such that in the desired operating flow range of the duct, the fluid entering the flush scoop is disturbed and as a result creates a low pressure region downstream of the louver. The low pressure region substantially eliminates the generation of any pressure pulses and acoustic resonance also known as Helmholtz resonance.

Flush inlet scoop design for aircraft bleed air system

A system and method of using a variable geometry ejector for a bleed air system using integral bleed pressure feedback which utilizes a minimal amount of high-pressure air, thus improving the overall engine cycle performance and is easily adaptable to a multitude of different engine types. This is accomplished through the use of a variable ejector using downstream pressure feedback to control the flow and pressure.

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Tempe, AZ, United States of America

Robert Romano