Honeywell International Inc.

Morris G Anderson

Grant A Gordon

Shawn Alstad

Yates Wong

Yogendra Y Sheoran

Danis Burton Smith

Robert Romano

John Taylor Pearson

Doug Hollingshead

Richard Bonvouloir

Zachary Ryan Price

Patrick Flynn

Narasimha Reddy Venkatarayappa

Murali Krishnan Payangapadan

Rama Sateesh Venkata Kandula

Merle L Sand

James B Cox

Nicholas A Everson

David K Jan

Steve Halfmann

Charles S Lo

Robert G Hoover

Justin C Mickelsen

George T Woessner

Christopher Zollars

Jason Garde

Matthew J Pohlman

Zedic Daniel Judd

Paul W Banta

William B Schuster

Danny Thomas Kimmel

Robert D Mitchell

Michael Albert McPherson

Jason A Gratton

George E Zurmehly

Mark Knowles

Robert Saunders Murray

Z Daniel Judd

David F Ross

Don Weir

Jeff M Mendoza

Tyler W Crowe

David Robinson

Laurence David Noble Liston

Ron Haugland

Hiroshi Kawamura

William E Alford

David K Winstanley

Matthew Dunn

Michael LaMar Trego

Allen Brown

Ted Alford

Dan Judd

John C Gerrard

Ron G Ruiz

Luis M Flamand

James W Brackin

David W Zmora

Peter Anthony

Dayakara Raju Perubandi

Daniel Brown

Swarna Sinha

Yogendrea Yogi Sheoran

Michael Albert Mcpherson

Michael L Trego

A gas turbine engine inlet anti-ice system includes a nacelle having an inlet lip, an anti-ice air supply duct, and a flow deflector. The inlet lip has an annular anti-icing chamber formed therein that is defined by an inner surface of the inlet lip and an aft wall that has an aft wall opening formed therein. The anti-ice air supply duct is configured to direct a flow of pressurized air into the aft wall opening. The flow deflector is coupled to the aft wall and extends over the aft wall opening. The flow deflector has an inner surface, an outer surface, a closed end, and an open end. The flow deflector and aft wall define a flow channel that extends between the closed end and the open end and in a direction that is tangential to the aft wall opening.

Shielded swirl gas turbine engine inlet anti-icing system

A muffler includes a housing defining a first chamber, a second chamber and a third chamber. The muffler includes at least a pair of nested protrusions in communication with an inlet. The pair of nested protrusions is coupled to a respective surface of a pair of plates disposed in the housing such that one of the pair of nested protrusions is spaced apart from and opposite another of the pair of nested protrusions to define a tortuous path that terminates at an outlet defined along an outer circumference. The first chamber is downstream from the pair of plates. The muffler includes a first tube fluidly coupled to the first chamber to direct the exhaust gases from the first chamber to the second chamber. The muffler includes a second tube fluidly coupled to the second chamber to direct the exhaust gases from the second chamber to the third chamber.

Muffler

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

A thermally isolated sensor associated with a gas turbine engine includes a sensor probe configured to measure a temperature of a fluid associated with the gas turbine engine, and a base to be coupled to the gas turbine engine. The thermally isolated sensor includes a leading projection coupled to the base that extends into the fluid. The leading projection is configured to be heated by a heat source associated with the gas turbine engine. The thermally isolated sensor includes a trailing projection coupled to the base that extends into the fluid. The trailing projection is downstream from the leading projection. The trailing projection includes an inlet, and the sensor probe is disposed within the inlet and thermally isolated from the leading projection.

Thermally isolated sensor for gas turbine engine

A method of health management and assessment for an air data probe comprises performing a calibration process for the air data probe prior to installation of the air data probe on a vehicle; performing an operational process after the air data probe is installed on the vehicle; computing residuals for individual pressure channels of the air data probe and an aggregated response function, based on outputs from the calibration process and the operational process; storing and trending the residuals over time; evaluating a trendline for the residuals against one or more threshold values; and announcing a message when one or more of the threshold values is exceeded, indicating that the health of the air data probe is compromised.

Method of health management and assessment for a multi-function air data probe

A bleed valve for a gas turbine engine includes a housing that defines an inlet upstream from an outlet. The bleed valve includes a poppet movable relative to the housing between a first position, in which the poppet closes the inlet, and a second position, in which the inlet is open and configured to receive a fluid flow. The housing defines a tortuous path for the fluid flow from the inlet to the outlet configured to reduce a pressure of the fluid flow from the inlet to the outlet within the housing. The tortuous path is defined by a plurality of rings positioned about the poppet, with each ring of the plurality of rings spaced apart from an adjacent ring of the plurality of rings between the inlet and the outlet to define the tortuous path.

Bleed valve with reduced noise

Method and systems of determining when to replace an air data probe are provided. The method includes estimating air data probe temperatures based at least in part on available vehicle sensor data; tracking an amount of time an estimated temperature of the heating element is within at least one temperature range; and providing an air data probe replacement indication when a replacement threshold is met that is at least in part based on reaching a cumulative amount of time the heating element has an estimated temperature within the at least one temperature range.

Air data probe replacement determination system

A multi-function air data probe comprises a probe stem having an outer surface that extends between a first end and an opposite second end, with the probe stem having a first cross-sectional diameter; and a probe head having an outer surface that extends between a proximal end and a distal end, wherein the proximal end of the probe head is coupled to the first end of the probe stem. The probe head has a second cross-sectional diameter that is larger than the first cross-sectional diameter of the probe stem. A plurality of multi-hole ports is located in the probe head, with the multi-hole ports extending into and through the probe stem. The air data probe is operative to make measurements used to determine one or more of angle of attack values, total pressure values, and static pressure values.

Multi-function air data probe having multi-hole ports used for determining angle of attack, total and static pressure values

A total air temperature (TAT) probe having a self-regulating heating system is provided. A TAT probe housing includes at least one heating cavity that is located proximate to a tip of the TAT probe. A heating element is received within the at least one heating cavity. The heating element is composed from a flexible material with a very high positive temperature coefficient (PTC) that provides non-linear resistance with temperature with generally relatively low electrical resistances at temperatures below freezing and relatively high electrical resistances above freezing. A power source is coupled to the heating element. The very high PTC material of the heating element causes less power to be drawn by the heating element from the power source at higher temperatures above freezing than the power drawn by the heating element from the power source at lower temperatures below freezing to maintain a desired temperature of the TAT probe.

Self-regulating heating system for a total air temperature probe

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 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

An air data probe is provided. The air data probe includes a pitot probe having a mounting base or flange, support strut, and tube with a forward facing inlet that is configured to capture a total pressure of the surrounding air, at least three dams placed within the tube of the pitot probe for blocking the ballistic trajectory of water droplets or ice crystals from passing directly through the tube to a downstream pressure sensing element, and a heater element integrated into the tube of the pitot probe on the outside of the dams. The at least three dams are oriented within the tube of the pitot probe in such a way that the dam locations are configured for two or more installations of the air data probe.

Arrangement of dams in air data probe

Embodiments of icing resistant total temperature probes with integrated ejectors are provided. One air data probe comprises: a base; a body having a leading and trailing edges: a first passage defining a first annulus; a temperature sensor within the first passage; a heat shield defining an exterior wall of at least part of the first passage, wherein the sensor is positioned within the shield; a second passage comprising a second annulus defined by a space between the shield and the body; an intake port having an intake aperture that opens to the first and second passages; a separate heated airflow passage, the heated airflow passage having an air input port configured to couple to an air supply source and following a path within the probe body; an integrated air ejector coupled to heated airflow passage to motivate air into the intake aperture and through the first and second air passages.

Icing resistance total temperature probe with integrated ejector

Systems and methods for icing resistant total air temperature probes are provided. In one embodiment, a total air temperature data probe comprises: a probe base; a probe body comprising: a first interior airflow passage comprising a first annulus; a temperature sensor positioned within the first annulus; a heating element; a notched intake port positioned at a distal end, wherein the probe body provides a conductive thermal path from the heating element to the intake port, the intake port including an open channel extending inward into an intake aperture of the probe body, and a cutaway region that defines a recessed second face inset from the first face and exposes the open channel at least partially from the leading edge. The notched intake port further comprises a slot inset from the recessed second face that traverses across at least a portion of the intake aperture perpendicularly to the open channel.

Systems and methods for icing resistant total air temperature probes

A probe portion of an air data probe is provided. The probe portion includes an endoskeleton structure having an outer surface, a heater cable disposed along the outer surface of the endoskeleton structure, a porous cover, surrounding the endoskeleton structure and heater cable, and a braze filler that substantially fills gaps between the heater cable and the endoskeleton structure and that substantially fills gaps in the porous metal cover.

Forming an air data probe from a porous cover and brazing material

Growing community of inventors

Mesa, AZ, United States of America

Morris G Anderson