United Technologies Corporation

Raytheon Technologies Corporation

Rtx Corporation

Nigel David Sawyers-Abbott

Matthew Exner

Frederick M Schwarz

Todd A Davis

Steven H Zysman

Armando Amador

Zhong Ouyang

Ron I Prihar

Garrett Kernozicky

James Power

Kevin W Schlichting

Anthony R Bifulco

Jonathan Gilson

Gregory E Reinhardt

Joel H Wagner

Denman H James

Michael Joseph Murphy

Dilip Prasad

Federico Papa

Amr Ali

Constantino V Loffredo

Andrew A Consiglio

Lawrence P Roberts

Joseph P Foster

Charles Waldo Haldeman, Iv

Andre L Bent

Priscilla Chin

Kenneth N Baker

Adam F Knapp

Charles Waldo Halderman Iv

Frederico Papa

PhD Kenneth N Baker

A seal system has: a first member; a seal carried by the first member and having a seal face; and a second member rotatable relative to the first member about an axis. The second member has: a seat on a first piece of the second member, the seat having a seat face in sliding sealing engagement with the seal face; and a radially outwardly closed collection channel for collecting centrifuged oil; a second piece encircling and attached to the first piece and having a circumferential array of apertures; and cooperating with the first piece to define a plenum; and a flowpath from the collection channel passing radially outward axially spaced from the seat face to cool the seat face and passing axially away from the seat face in the plenum.

Oil-cooled carbon seal

A method of determining a repair method for a defect in a bladed rotor can comprise comparing the defect in a three-dimensional model of an inspected integrally bladed rotor (IBR) to a plurality of known defects from a repair database; determining the defect is matching a known defect in the plurality of known defects in the repair database; and generating a repair process associated with the known defect in response to determining the defect is matching the known defect. A method can also comprise determining a potential repair process; performing a structural simulation of a finite element model for the inspected IBR with the potential repair; performing an aerodynamic simulation of an aerodynamic model for the inspected IBR with the potential repair; and generating the potential repair process for the defect in response to determining the inspected IBR with the potential repair meets structural and the aerodynamic criteria.

Blend approach based inspection and analysis systems and methods

An article of manufacture may include a tangible, non-transitory computer-readable storage medium having instructions stored thereon that, in response to execution by a processor, cause the processor to perform operations comprising: commanding, via the processor, a first scan of a bladed rotor; generating, via the processor, a three-dimensional model based on a first set of data received from a first scanner; comparing, via the processor, the three-dimensional model to an acceptable three-dimensional model of the bladed rotor; determining, via the processor, areas of interest based on the comparison; and commanding, via the processor, a contact probe to perform a non-destructive inspection on the areas of interest.

Multi-stage inspection systems and methods

A passive transpirational flow acoustic liner assembly for a gas turbine engine includes a guide vane assembly and a conduit configured to deliver airflow received from the guide vane. The guide vane assembly includes an airfoil having a transpirational flow acoustic liner. The acoustic liner includes a face sheet defining a portion of an outer surface of the airfoil and having a plurality of first apertures, a segmented member coupled to the face sheet and having a plurality of chambers in fluid communication with the outer surface via the plurality of first apertures, a backing sheet having a plurality of apertures and being coupled to the segmented member such that the segmented member is positioned between the face sheet and the backing sheet, and a plenum coupled to the backing sheet opposite the segmented member and fluidly connected to the conduit.

Passive transpirational flow acoustically lined guide vane

A lubrication system for a gas turbine engine includes a primary fluid tank to receive a primary fluid, at least one secondary fluid tank to receive at least one fluid additive, and a mixer. The mixer has at least a first inlet in fluid communication with the primary fluid tank and a second inlet in fluid communication with the at least one secondary fluid tank. The mixer has at least one outlet that delivers a mixture of the primary fluid and the at least one fluid additive to a gas turbine engine component.

Fluid additive system

A vane for use in a gas turbine engine includes an airfoil having a suction side and a pressure side, and a transpirational flow acoustic liner disposed in the airfoil. The liner includes a face sheet defining a portion of an outer surface of the airfoil and having a plurality of first apertures, a segmented member coupled to the face sheet, and a backing sheet coupled to the segmented member the segmented member such that the segmented member is positioned between the face sheet and the backing sheet. The segmented member includes a plurality of chambers in fluid communication with the outer surface via the plurality of first apertures. The backing sheet has a plurality of second apertures.

Active flow control transpirational flow acoustically lined guide vane

An environmental sampling system includes a passage in an aircraft component and a removable collector disposed in the passage. The passage has an inlet at a first region and an outlet at a second region. When the aircraft component is in operation the first region is at a greater pressure than the second region such that air flows through the passage from the inlet to the outlet. The removable collector is configured to retain constituents from the air and to react with the media designed to mimic corrosion effects seen at higher temperatures on engine parts. The constituents can then be characterized and correlated to engine deterioration to predict maintenance activity.

Environmental sampling system and method

A turbofan engine may comprise an inlet and a fan case coupled to the inlet. An engine case may be coupled to the fan case via a vane extending between the fan case and the engine case. A strut apparatus may extend from the fan case and limit deflection of the fan case. The strut apparatus may comprise a first end proximate the fan case, and a second end coupled to at least one of the engine case or a structure for mounting the turbofan engine to an aircraft.

Inlet cowl deflection limiting strut

A gas turbine engine component includes a first member, a second member rotatable relative to the first member about an axis, and a seal assembly that includes a seal supported by the first member and a seal runner that rotates with the second member relative to the seal. The seal runner includes at least one internal passage to direct cooling fluid flow through the seal runner. A restriction is associated with the at least one internal passage to restrict flow through the at least one internal passage in response to an engine condition.

Seal runner flow damper

A gas turbine engine includes a turbine and a compressor in rotational communication with the turbine via a shaft. The shaft is rotatable about a longitudinal centerline and includes a first axial end and a second axial end opposite the first axial end. The gas turbine engine further includes a first bearing compartment including a first compartment casing detachably mounted axially outside the compressor and the turbine. The first bearing compartment is in contact with the first axial end of the shaft and includes a first bearing which rotatably supports the shaft. The first bearing compartment is self-contained such that an internal lubrication system of the first bearing compartment is fluidally isolated from a remainder of the gas turbine engine outside the first bearing compartment.

Modular bearing compartment

A gas turbine engine includes an engine core having a compressor, a combustor fluidly connected to the compressor, and a turbine fluidly connected to the combustor. A core nacelle is disposed radially outward of the engine core. A cavity is disposed between an inner surface of the core nacelle and an outer surface of the engine core. The cavity includes a vent disposed at an aft end. The vent includes at least one flap configured to be maintained in an unrestricted position and in a restricted position. An actuator is configured to control the position of the at least one flap.

Modulated fire extinguishing vent for a gas turbine engine

A gas turbine engine comprises a fan rotor having fan blades received within an outer nacelle, and the outer nacelle having an inner surface. The outer nacelle is secured to an inner portion through a mount flange at a first axial location. An acoustic treatment extends inwardly of the outer portion of the nacelle and across the axial location of the mount flange and further inwardly toward the fan blades.

Gas turbine engine with one piece acoustic treatment

The present disclosure relates generally to a thrust reverser for a gas turbine engine. As a translating cowl is translated aft from the nacelle of the gas turbine engine, a cascade is also translated in the aft direction and a blocker door coupled to the cascade is pivoted into a fan duct by means of a camming surface, thereby diverting air in the fan duct through the cascade. In the stowed position, both the cascade and the blocker door are disposed radially outward of a radially inner wall of the nacelle and/or the translating cowl.

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South Glastonbury, CT, United States of America

Nigel David Sawyers-Abbott