United Technologies Corporation

Raytheon Technologies Corporation

Rtx Corporation

Om Parkash Sharma

Gabriel L Suciu

Lawrence A Binek

Edward F Pietraszkiewicz

Jesse R Boyer

Evan J Butcher

Vijay Narayan Jagdale

Bryan Galbraith Dods

Brian D Merry

Michael F Blair

Frank J Cunha

Dmytro Mykolayovych Voytovych

Georgi Kalitzin

Jesse M Chandler

Joseph Brent Staubach

Zaffir A Chaudhry

Andrzej Ernest Kuczek

Matthew R Feulner

Simon W Evans

Michael M Joly

William D Sprout

John A Raw

Martin Graf

Mark Barnett

Frederick M Schwarz

Daniel L Gysling

Christopher Marc Dye

Marc J Muldoon

William K Ackermann

Wesley K Lord

Tahany Ibrahim El-Wardany

Lawrence E Portlock

Ioannis Alvanos

Alexander Staroselsky

Dilip Prasad

Shankar S Magge

Matthew E Lynch

David Lei Ma

Catalin G Fotache

Sanjay S Hingorani

Gorazd Medic

Gary M Stetson

Kevin M Eveker

Carl N Nett

William E Alford

Charles R LeJambre

Kar D Chin

P William Baumann

Jeffrey B Gertz

Junsok Yi

Charlie R Lejambre

An airfoil for a gas turbine engine including an airfoil body extending between a leading edge and a trailing edge and between a pressure side and a suction side. The airfoil body includes a strut portion extending from the leading edge and a flap portion extending from the trailing edge. The flap portion is pivotable relative to the strut portion. A flexible skin surrounds both the strut portion and the flap portion on both the pressure side and the suction side.

Morphing structures for fan inlet variable vanes

A blended wing aircraft including a blended wing fuselage and at least one embedded gas turbine engine in the fuselage. The gas turbine engine includes an inlet duct formed with a generally elliptical shape that includes a first set of ellipse sections along an upper portion of the inlet duct and a second set of ellipse sections along a lower portion of the inlet duct. The inlet duct includes a vertical centerline. The first set of ellipse sections at a throat of the inlet duct is larger in area than an area of an upstream most end of the second set of ellipse sections. The area of the second set of ellipse sections increases toward a downstream end of the inlet duct. A fan section has an axis of rotation that is spaced from the vertical centerline and is disposed within an inlet duct orifice. The inlet duct is upstream of the fan section.

Gas turbine engine inlet wall design

A process for additively controlled surface features of a gas turbine engine casing. The process comprises forming the casing having an inner surface and an outer surface opposite the inner surface; forming a surface feature on the casing proximate the inner surface, wherein the surface feature comprises a structure on the inner surface configured to align or misalign with respect to a flow direction of a working fluid in a flow path of the casing.

Additively controlled surface roughness for designed performance

A gas turbine engine includes a fan section, a compressor section, and a turbine section. The fan section has a plurality of vane assemblies spaced circumferentially about an engine axis. The vane assemblies each include an airfoil extending between a leading edge and a trailing edge, a control rod extending through the airfoil, and a mechanism driven by the control rod to change the shape of the airfoil. A vane system for a gas turbine engine is also disclosed.

A hybrid electric gas turbine engine includes a fan section having a fan, a turbine section having a turbine drivably connected to the fan through a main shaft that extends along a central longitudinal axis, a gas generating core extending along a first axis that is radially offset from the central longitudinal axis, and an electric motor drivably connected to the main shaft, wherein the electric motor is colinear with the main shaft.

Systems and methods for hybrid electric turbine engines

An additively manufactured thermally insulating structure comprising a base layer and a fire-resistant layer adjacent to the base layer that forms an air gap therebetween. A method for assembling a miniature gas turbine engine includes additively manufacturing an additively manufactured thermally insulating structure onto a static structure of the miniature gas turbine engine.

Additively manufactured thermally insulating structure

A vehicle structure with unitary casing for an attritable gas turbine engine comprising a vehicle structure forming a unitary casing having a casing wall opposite the vehicle structure; a bypass duct formed between the casing wall and the vehicle structure, wherein the unitary casing is configured to receive a core of the attritable gas turbine engine.

Attritable engine integrated with vehicle

A gas turbine engine is provided that includes a compressor section, a turbine section, and a unitary structure. The compressor section has at least one compressor rotor stage. The turbine section has at least one turbine rotor stage. The compressor rotor stage and the turbine rotor stage are in rotational communication with each other. The unitary structure includes an outer case portion, a combustor section, a turbine nozzle, and an exhaust duct. The unitary structure configured for attachment with the turbine section and compressor section.

Gas turbine engine with a unitary structure and method for manufacturing the same

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 gas turbine engine includes an inlet duct that is formed with a generally elliptical shape. The inlet duct includes a vertical centerline and a fan section that has an axis of rotation. The axis of rotation is spaced from the vertical centerline and is disposed within an inlet duct orifice.

An embodiment of a fan blade includes an interior region between a metallic pressure sidewall and a metallic suction sidewall. Each sidewall extends in span from a base to a tip, and extends in chord from a leading edge to a trailing edge. The interior region of the fan blade includes a first fully dense metallic portion and a first porous metallic portion. The first fully dense metallic portion has a volume occupying at least 10% of a total volume of the interior region, and substantially no porosity. The first porous metallic portion is integrally joined to the fully dense metallic portion, and is selected from a structured lattice, an unstructured foam, and combinations thereof.

Gas turbine engine fan blade, design, and fabrication

An exemplary gas turbine engine includes a turbine section and a fan mechanically connected to the turbine section such that rotation of the turbine drives rotation of the fan. The fan includes a hub, a plurality of blade bodies extending radially outward from the hub to a first partial shroud, and a plurality of blade tips extending radially outward from the partial shroud.

Partially shrouded gas turbine engine fan

A compressor section for use in a gas turbine engine comprises a compressor rotor having a hub and a plurality of blades extending radially outwardly from the hub and an outer housing surrounding an outer periphery of the blades. A tap taps air at a radially outer first location, passing the tapped air through a heat exchanger, and returning the tapped air to an outlet at a second location which is radially inward of the first location, to provide cooling air adjacent to the hub. A gas turbine engine is also disclosed.

Compressor core inner diameter cooling

An exemplary gas turbine engine includes a turbine section operative to impart rotational energy to a compressor section. The turbine section includes at least a low-pressure turbine and a high-pressure turbine, and a number of stages in the low pressure turbine is from three to five.

Blades in a turbine section of a gas turbine engine

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South Windsor, CT, United States of America

Om Parkash Sharma