Honeywell International Inc.

Alliedsignal Inc.

Honeywell G.m.b.h.

Yogendra Y Sheoran

Bruce Dan Bouldin

Daniel V Brown

Zedic Daniel Judd

John Taylor Pearson

Cristopher Frost

Yates Wong

Jennifer Ann Reich

Nicholas A Williams

Jeffrey Hein

Cecilia Lam

Benjamen Kurt Higuera

Andrew Stephen Peduchi

Ravisha Pramod Sellahewa

Eduardo Guerra

Ora Morency Cowans

Morris G Anderson

Marc Schmittenberg

Yoonshik Shin

Todd A Kincheloe

Daniel Aukland

Eric Blumer

Shakeel Nasir

David Chou

Mahmoud Mansour

William Facinelli

Doug Hollingshead

John Meier

Vighneswara Rao Kollati

John Schugardt

Z Daniel Judd

David H Edmonds

Kyle D Asplund

Craig A Lyon

Vunnam Kiran

John G Zimmerer

Mark C Morris

Paul T Wingett

Nick A Nolcheff

Ardeshir Riahi

Daniel Cregg Crites

Louie Timothy Gaines

Emray R Goossen

Bjoern Schenk

Frank Lin

Bradley Reed Tucker

Jeff Howe

Gary L Boyd

Mark Matwey

Peter Hall

Charles Michael Royalty

Shezan Kanjiyani

Adam Kowal

Jun Isobe

Timothy Ertz

Reha Gomuc

Devinder N Katariya

John Thurston

Robert Saunders Murray

Craig E Thompson

David F Ross

Murali Krishnan Payangapadan

Kevin S Dittmar

Ramalingam Pavadai Nallur

Jeffrey A Turner

Rob Robbins

Tyler W Crowe

Don Reginald Holcomb

Alan Kang

Shailesh Kumar

Mario Alejandro Hidalgo

Chuck Royalty

Don Weir

Lori Wheeler

Joseph W Michalski, Jr

Andrew Earl

Walter L Blackmore

Marcos Alazraki

Tirumala Rao Koka

Lance Callen

Patrick Trizila

Roger I Payne

Matt Greenman

Douglas Hollingshead

Timothy R Whittemore

Bert A Diehl, Jr

Knauer E Chad

Walid M Boulos

D Warren Sumner

Thomas W Davis

Kurt T Kenzler

Ramalingam Nallur

Brian Hesano

Lee Glascoe

Don Reginald Holcomb, Jr

Karthik Narayanasamy

Lavan Kumar Gundeti

John Pfligler

Bradley Tucker

A ported shroud for a compressor associated with a gas turbine engine includes a primary inlet configured to be in fluid communication with the compressor, and the primary inlet is defined to extend along a central axis of the ported shroud. The ported shroud includes a bellmouth that surrounds the primary inlet, and a port plenum configured to be in fluid communication with the compressor. The port plenum extends along an axis that is transverse to the central axis of the ported shroud and transverse to a direction of fluid flow. The port plenum has a port plenum inlet defined about the axis, and the port plenum inlet is defined through the bellmouth such that a tortuous path is defined to the port plenum inlet. The port plenum including a port plenum outlet downstream from the port plenum inlet configured to be in fluid communication with the compressor.

Compressor ported shroud with particle separator

An asymmetric inlet particle separator for a gas turbine engine includes an inlet having a first cross-sectional shape, and a duct downstream of the inlet. The duct includes a bend upstream from a splitter, a scavenge branch and an engine airflow branch. The splitter is outside of a line of sight from the inlet and the splitter separates the scavenge branch from the engine airflow branch. The asymmetric inlet particle separator includes an annulus downstream of the engine airflow branch configured to be coupled to the gas turbine engine. The annulus has a second cross-sectional shape, and the engine airflow branch transitions from the first cross-sectional shape to the second cross-sectional shape.

Asymmetric inlet particle separator for gas turbine engine

A particle separator includes a housing through which a flow stream is directed. A number of guide vanes are disposed in the housing. The guide vanes have a profile wherein the flow stream is guided to follow the profile. The guide vanes have a wall surrounding an open interior that defines a vane plenum. A plurality of through-holes extend through the wall of the guide vane. The through-holes are open to the flow stream and to the vane plenum. A duct connects with the vane plenum and is configured to discharge particles collected in the vane plenum.

Self refreshing particle separator

A method for scavenging small particles from a turbine engine includes directing compressed air through a flowpath, downstream of a compressor, which causes a reduction in a radial flow component and the introduction of or an increase in an axial flow component of the compressed air, removing a portion of the compressed air from the flowpath and directing the portion into a scavenge plenum, the scavenge plenum being positioned adjacent to and radially outward from the flowpath, and returning the portion of the compressed air from the plenum to the flowpath while maintaining a majority of the small particles that were present in the portion within the scavenge plenum. Further, the method includes removing the majority of small particles from the plenum. The step of removing occurs intermittently during engine operation, during engine shutdown, or while the engine is not in operation, but does not occur continuously during engine operation.

Scavenge methodologies for turbine engine particle separation concepts

A particle separator associated with a compressor section of a gas turbine engine includes a duct that defines a fluid flow path from a diffuser to a deswirl section. The duct includes a curved portion between an outlet of the diffuser and an inlet of the deswirl section. The curved portion is configured to have at least one low velocity region and a high velocity region. The particle separator includes at least one cluster of inlet passages defined at the at least one low velocity region. The particle separator includes a scavenge plenum coupled to the duct and in fluid communication with the at least one cluster of inlet passages. At least one outlet slot is defined through the duct downstream of the at least one cluster of inlet passages in the high velocity region and is in fluid communication with the scavenge plenum.

Compressor particle separator for gas turbine engine

An inlet particle separator system for a gas turbine engine includes a separator manifold. The separator manifold includes an inlet upstream from an outlet. The inlet is to receive an incoming airflow, and the outlet is to be fluidly coupled to an inlet of the gas turbine engine. The inlet particle separator system includes at least one dry fog nozzle coupled proximate the inlet so as to face at least partially away from the inlet. The dry fog nozzle is external to the separator manifold, and the dry fog nozzle is to direct a spray of dry fog in a direction transverse to the incoming airflow to agglomerate with fine particles in the incoming airflow to form agglomerated particles. The inlet particle separator system includes a scavenging system coupled to the separator manifold downstream from the inlet, and the scavenging system removes the agglomerated particles from the separator manifold.

Systems and methods for dry fog inlet particle separator

A gas turbine engine includes a combustion section that generates combustive gases that form a primary exhaust flow and an exhaust system downstream from the combustion section. The exhaust system includes an eductor system that includes a body that extends along a first axis, and a plurality of ducts spaced apart about a circumference of the body. Each of the plurality of ducts define a plurality of eductor primary flow paths that terminate in a mixing chamber. The exhaust system includes a muffler system downstream from the mixing chamber that includes a plurality of baffles that cooperate to define a tortuous path and attenuate sound generated by the gas turbine engine. The exhaust system includes a housing that surrounds the eductor system and the muffler system such that the eductor system and the muffler system are contained within the housing.

Exhaust systems and methods for gas turbine engine

A particle separator includes a housing defining an inlet and an outlet. A flow stream is directed from the inlet to the outlet. A number of dividers are disposed in the housing and separate flow channels from each other. The flow channels extend from the inlet to the outlet. The dividers each have a profile so that the flow channels follow the profile. The dividers each include a plurality of cavities that open to each of the flow channels and that have blind ends. The cavities each have an aspect ratio greater than one, and are configured to collect particles from the flow stream.

Driven cavity particle separator

Airfield guidance signs are described herein. One airfield guidance sign includes a first surface, a second surface angled with respect to the first surface, and a top edge adjacent the first surface and the second surface, wherein the top edge is rounded to reduce a pressure differential between the first surface and the second surface when a force is applied to the first surface or the second surface.

Airfield guidance signs

Systems and methods for an exhaust system for a gas turbine engine are provided. The method includes: receiving a primary exhaust fluid in a primary manifold; receiving a secondary cooling fluid in a secondary plenum; directing the primary exhaust fluid through a plurality of eductor primary flow paths associated with a respective plurality of ducts spaced circumferentially about a primary manifold, the plurality of eductor primary flow paths extending through the secondary plenum; and mixing the primary exhaust fluid and the secondary cooling fluid in a mixing chamber associated with a respective one of the plurality of ducts to create a mixed fluid flow.

An inertial inlet particle separator system for a vehicle engine is provided. A separator assembly and collector assembly are coupled to the scavenge flow path and configured to receive the scavenge air. The collector inlet has a throat defining a cumulative throat area at each position along the throat length from the first throat end to the second throat end. The collector body defines a cross-sectional area associated with each position along the throat length between the first throat end and the second throat end. The collector outlet is coupled to the collector body such that scavenge air flows into the collector inlet, through the collector body, and out through the collector outlet. At a first position between the first throat end and the second throat end, the respective cross-sectional area of the collector body is greater than or equal to the respective cumulative throat area.

Inlet particle separator systems and methods

A flow control system in an inlet duct to a heat exchanger includes a door having a first end and a second end opposite the first end. The first end rotates about an axis and the second end moves between an open position and a closed position to respectively allow and prevent flow into the heat exchanger. The second end has a rounded configuration. A plurality of mixing elements are downstream of the door. At least one mixing element has a base portion and a distal portion, and the base portion has a base width and the distal portion has a distal width. The base width is wider that the distal width.

Method and apparatus for flow maldistribution control

An outflow valve is provided. The outflow valve includes a frame and a first door rotatably coupled to the frame. The first door has a first side opposite a second side and a bellmouth. The bellmouth is defined by a super-ellipse, with a major axis of the super-ellipse substantially parallel to the second side and a minor axis of the super-ellipse substantially perpendicular to the second side. The outflow valve also includes a second door rotatably coupled to the frame. The first door and the second door are substantially simultaneously movable between at least a first position and a second position.

Outflow valve having super-elliptical bellmouth

A turbine engine incorporating a fine particle separation means includes a radial compressor that rotates about a longitudinal axis, a radially-oriented diffuser located downstream and radially outward, with respect to the longitudinal axis, from the radial compressor, and a flow path positioned downstream and radially outward, with respect to the longitudinal axis, from the diffuser, wherein the flow path comprises an outer annular wall and an inner annular wall between which the compressed air flows, and wherein the flow path comprises an arc the redirects the compressed air from flowing in a substantially radial flow direction to a substantially axial flow direction. The turbine engine further includes an extraction slot in the outer annular wall that fluidly connects with a scavenge plenum, the scavenge plenum being positioned adjacent to and radially outward from the outer annular wall at a position downstream axially along the flow path from the arc.

Turbine engine designs for improved fine particle separation efficiency

Systems and methods for an exhaust system for a gas turbine engine are provided. The exhaust system includes an eductor system adapted to receive a primary exhaust fluid. The eductor system includes a body that extends along a first axis, with a plurality of ducts spaced apart about a circumference of the body. Each of the plurality of ducts extend from the body along a second axis transverse to the first axis to define a plurality of eductor primary flow paths that terminate in a mixing chamber. The mixing chamber is adapted to receive a secondary cooling fluid and to mix the primary exhaust fluid with the secondary cooling fluid to create a mixed fluid flow.

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Scottsdale, AZ, United States of America

Yogendra Y Sheoran