United Technologies Corporation

Raytheon Technologies Corporation

Steven Clarkson

Thomas J Robertson, Jr

Mark W Costa

Colin J Kling

Michael Parkin

Paul Thomas Rembish

Daniel K Van Ness

JinQuan Xu

Grant O Cook, Iii

Wendell V Twelves

Glenn Levasseur

James T Roach

Barry Barnett

Charles R Watson

Christopher J Hertel

Carl Brian Klinetob

Phillip Alexander

Scot Adams Webb

Matthew A Turner

Shari L Bugaj

Sreenivasa R Voleti

Richard B Bergethon

Michael Caulfield

Daniel L Van Ness

Jr Thomas J Robertson

Daniel K Van Ness Ii

Plated polymeric gas turbine engine parts and methods for fabricating lightweight plated polymeric gas turbine engine parts are disclosed. The parts include a polymeric substrate plated with one or more metal layers. The polymeric material of the polymeric substrate may be structurally reinforced with materials that may include carbon, metal, or glass. The polymeric substrate may also include a plurality of layers to form a composite layup structure.

Plated polymer fan

A case for a gas turbine engine includes a case body defining an axially extending core flow path, a radially extending bleed air duct coupling the core flow path in fluid communication with the external environment, and a structure-supporting member spanning the bleed air duct. A lubricant conduit is connected to the case body and is in thermal communication with the structure-supporting member.

Gas turbine engines with heated cases

A blade containment system includes a plurality of circumferentially-arranged rotatable blades. Each blade has a blade compliance. An annular containment structure is arranged around the rotatable blades. The containment structure includes a liner that has a liner compliance. The blade compliance and the liner compliance are configured such that a strain induced on a respective one of the blades upon impact with the liner is less than a threshold critical strain beyond which the rotatable blades fracture.

Reduced fan containment threat through liner and blade design

A fan case includes a composite fan case body including an outer surface and at least one attachment tool attached to the outer surface of the fan case body. The attachment tool includes a boss that has at least one fastener opening with a threaded insert. A channel extends from at least one interior cavity of the attachment tool through an outer wall of the attachment tool.

Bolt attachment to composite fan case

A method for installing a mounting hole through a wall of a fan case of a gas turbine engine is disclosed. The method may comprise: 1) installing a pilot hole through the wall of the fan case at an angle perpendicular to an outer surface of the wall, 2) inserting a boss through the pilot hole, 3) bonding the boss to the wall of the fan case, and 4) installing the mounting hole through the boss at an off-axis angle with respect to the angle perpendicular to the outer surface of the wall.

Instrumentation boss for fan containment case

An ice liner assembly for a fan containment case for a turbofan gas turbine engine is disclosed. The disclosed ice liner assembly includes a plurality of arcuate panels arranged end to end to form a cylindrical liner that is disposed within the fan containment case and aft of the fan and abradable strip liner that circumscribes the fan. Because the plurality of arcuate panels are arranged end to end fashion, the ice liner assembly includes a plurality of splice joints, or a joint between two abutting ends of two arcuate panels. The splice joints are reinforced with molded polymeric splice support cores that are substantially lighter and less expensive than currently employed high density aluminum honeycomb core materials.

Fan case ice liner for turbofan engine

A turbine engine fan case () comprises a composite body member () circumscribing an axis () and having an annular mounting portion (), a segmented polymer member () along the annular mounting portion, and integrated therewith.

Fan cases and manufacture methods

A nose cone may have a spinner including a main portion and an axially extending stepped portion. The nose cone may also have an annular aft support ring radially secured to the axially extending stepped portion. The nose cone may further include a fairing, which may be secured to the stepped portion.

Nose cone with an aft support ring for radial attachment

A mount for mounting a component to a gas turbine engine is disclosed. The mount may include a central portion that attaches to the component, and a flange circumscribing the central portion and extending to the gas turbine engine, the flange including a fusible region that breaks at a predetermined load. A method for protecting a component mounted to a gas turbine engine is also disclosed. The method may include attaching a mount to a casing of the gas turbine engine, the mount including a fusible region that breaks at a predetermined load. The method may further include attaching the component to the mount. The method may further include the fusible region breaking when the mount experiences the predetermined load, detaching the component from the casing of the gas turbine engine.

Auxiliary component mount including a fusible region configured to break at a predetermined load

A turbofan engine has a fan having a circumferential array of fan blades. A fan case encircles the fan. There is at least one compressor section, a combustor, and at least one turbine section. The fan case comprises a containment case and a cartridge liner carried therein. A ballistic liner encircles at least a portion of the cartridge liner and is attached thereto.

Flowpath cartridge liner and gas turbine engine including same

A case for a gas turbine engine includes a core body. The core body defines a longitudinally extending core flow path, a laterally extending bleed air duct coupling the core flow path in fluid communication with the external environment, and a structure-supporting member spanning the bleed air duct. A heating element is connected to the core body and is in thermal communication with the structure-supporting member.

Core case heating for gas turbine engines

A core for a fan containment includes an intermediate core segment and a plenum for fluid passage defined through the intermediate core segment. The intermediate core segment has an axial inlet side, an axial outlet side opposed to the axial inlet side, a radially inner side, and a radially outer side opposed to the radially inner side. The radially outer side is configured to be operatively connected to a cylindrical outer case and the radially inner side is configured to be operatively connected to at least one arcuate panel to form a liner assembly. The plenum extends through the intermediate core segment proximate the radially outer side for fluid passage between the axial inlet side and the axial outlet side.

Core drainage systems for fan case assemblies

A method of manufacturing a fan case with a liner includes the steps of providing a preform having a circular cross-section with a cut and a first diameter, flexing the preform to reduce the first diameter to a second diameter, and adhering the preform to an inner surface of a fan case. A fan case for a gas turbine engine includes a fan case body having an inner surface. A preform is adhered to the inner surface and has a cut providing a gap.

Fan case ballistic liner and method of manufacturing same

A turbine engine fan case assembly includes a structural case and a liner assembly. A radially accommodating attachment system connects the liner assembly to the structural case. The attachment system comprises a circumferentially-distributed plurality of longitudinally elongate radially outwardly open channels mounted to the liner assembly. The attachment system further comprises an associated plurality of inwardly-projecting tongues mounted to the structural case. Each tongue is accommodated in an associated such channel.

Growing community of inventors

Cheshire, CT, United States of America

Steven Clarkson