United Technologies Corporation

Raytheon Technologies Corporation

Hamilton Sundstrand Corporation

Otis Elevator Company

Gulfstream Aerospace Corporation

Dilip Prasad

Gorazd Medic

Zaffir A Chaudhry

Bruce L Morin

Michael M Joly

Andrzej Ernest Kuczek

David A Topol

Jayant Sabnis

Simon W Evans

Georgi Kalitzin

Jinzhang Feng

Wesley K Lord

John P Wesson

Edward J Gallagher

Thomas M Zywiak

Harold W Hipsky

William A Veronesi

Murtuza Lokhandwalla

Richard A Poisson

Matthew E Bintz

Om Parkash Sharma

Nigel David Sawyers-Abbott

Eric Chrabascz

Mark Steven Thompson

Pedro S Baranda

Dmytro Mykolayovych Voytovych

John T Pitts

Paul A Stucky

Ary O Mello

Yuan Dong

John M Maljanian

Young Kyu Park

Constantine Baltas

Sue-Li Chuang

Sanjay S Hingorani

Gavin Hendricks

Derek J Michaels

Clas A Jacobson

William C Perron

Douglas C Mathews

Jayant S Sabnis

George M Bollas

Anil Prasad

John Michael Feiereisen

Kyle Palmer

Thomas J Ouellette

Brice N Cassenti

Junsok Yi

Randy Hull

Brad Crome

Young K Park

Adam Tate

Thomas Rothermel

Suman Das

Gorzad Medic

Zaffir A Chaudry

Jr John M Maljanian

Jr Ary O Mello

An assembly is provided for an aircraft propulsion system. This assembly includes a gas turbine engine and a vapor absorption refrigeration system. The gas turbine engine includes a turbine section. The vapor absorption refrigeration system is configured to be driven by waste heat energy received from the turbine section. The vapor absorption refrigeration system includes a condenser.

Aircraft propulsion system with vapor absorption refrigeration 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

A compressor with negative coefficient of thermal expansion case material comprising a rotor having blades with tips, the case including an inner case comprising a negative coefficient of thermal expansion material, and a tip clearance located between the tips and the inner case; wherein the tip clearance is maintained responsive to a flow of air over the negative coefficient of thermal expansion material.

Negative thermal expansion compressor case for improved tip clearance

A casing treatment comprising a hub having a surface, the hub being rotatable about an axis within a casing of a gas turbine engine compressor, at least one spiral groove formed in the surface extending axially relative to the axis, a stator blade fixed to the casing, wherein a tip of the stator blade is proximate to the at least one spiral groove.

Spiraling grooves as a hub treatment for cantilevered stators in compressors

A stator vane for a gas turbine engine section includes a stator vane having an airfoil extending between a leading edge and a trailing edge. The airfoil has a suction side and a pressure side. There is at least one piezoelectric actuator for changing a shape of at least one of the leading edge and the trailing edge. A gas turbine engine is also disclosed.

Gas turbine engine with morphing variable compressor vanes

A gas turbine engine includes a plurality of blades circumferentially spaced from each other. A plurality of rings are spaced radially outward from the plurality of blade. At least one actuator is in mechanical communication with the plurality of rings for moving the plurality of rings in an axial direction to create an axial gap adjacent at least one of the plurality of rings.

Adaptive case for a gas turbine engine

A compressor for use in a gas turbine engine including: an airfoil configured to rotate about an engine central longitudinal axis of the gas turbine engine; a casing, the casing including a radially inward surface; and a groove located within the casing opposite the airfoil, the groove is recessed in a radially outward direction from the radially inward surface of the casing, wherein the groove is defined by a forward groove wall, an aft groove wall opposite the forward groove wall, and a base groove interposed between the forward groove wall and the aft groove wall, and wherein the forward groove wall is operably shaped to generate an aft directed jet.

Inclination of forward and aft groove walls of casing treatment for gas turbine engine

A morphing aerodynamic control surface geometry comprising a control surface having an articulated portion comprising a flexible skin coupled at an exterior of the articulated portion, the flexible skin comprising opposed interlocking elements sandwiched within a flexible polymer coupled to the interlocking elements; wherein the flexible skin is configured compliant responsive to an articulation of the articulated portion.

Adaptive morphing engine geometry

A gas turbine engine includes an engine core having a compressor section, a combustor fluidly connected to the compressor section, and a turbine section fluidly connected to the combustor section. At least one compressor bleed connects a compressor flowpath with a first cooled cooling air path. The first cooled cooling air path includes a supplementary coolant injector connected to a supplementary coolant supply. The cooled cooling air path including a portion exterior to the engine core.

Injection cooled cooling air system for a gas turbine engine

A variable vane assembly may comprise a first vane and a second vane. The first vane may comprise a first strut portion and a first flap portion. The first flap portion may be configured to pivot relative to the first strut portion. The second vane may comprise a second strut portion and a second flap portion. The second flap portion may be configured to pivot relative to the second strut portion. The first flap may be configured to pivot independently of the second flap.

Variable vane assemblies configured for non-axisymmetric actuation

Disclosed is a flutter damper, including an acoustic liner configured for peak acoustical energy absorption at a frequency range that is greater than a frequency range associated with fan flutter, a chamber, and a piezoelectric element disposed within a first surface of the chamber, and the chamber being configured for peak acoustical energy absorption at a frequency range that is associated with one or more fan flutter modes, and wherein the piezoelectric element is operatively connected to an electronic engine control.

Flutter damper for a turbofan engine

Disclosed is a flutter damper including a first plurality of chambers configured for peak acoustical energy absorption at a frequency range that is associated with a first fan flutter mode, the first plurality of chambers in fluid communication with a flow surface, and a second plurality of chambers configured for peak acoustical energy absorption at a frequency range that is associated with a second fan flutter mode, the second plurality of chambers in fluid communication with the flow surface, and wherein the first plurality of chambers and second plurality of chambers are disposed in a grid pattern.

Flutter inhibiting intake for gas turbine propulsion system

A computer-implemented method for designing a built-in test is described. The method includes receiving, via a processor, a subsystem model including system parameters for a heat exchanger, wherein each of the system parameters includes a sensor variance; determining, via the processor, a test design vector based on one or more of the system parameters; and designing, via the processor, the built-in test based on the test design vector.

Plate-fin heat exchanger fouling identification

A particle separation device to remove particulate matter from an exterior air flow for use with an environmental control system includes a curved airflow path with an inner radius and an outer radius, the curved air flow path to receive the exterior air flow, a particle passage disposed along at least one of the inner radius and the outer radius to receive the particulate matter from the exterior air flow, a circumferential volute to receive the particulate matter from the particle passage, and a duct to transport the particulate matter from the circumferential volute to a downstream region.

Particle separation system

In accordance with one aspect of the disclosure, a rotor for a gas turbine engine is disclosed. The rotor may include a rotor disk and a plurality of blade extending radially outward from the rotor disk. At least one of the blades may have a physical nonuniformity. The blades may be distributed about the rotor disk based on any physical nonuniformities of the blades to generate at least one decay-resistant harmonic.

Gas turbine blade array with reduced acoustic output

Growing community of inventors

North Granby, CT, United States of America

Dilip Prasad