United Technologies Corporation

Raytheon Technologies Corporation

Rtx Corporation

Mark W Costa

Thomas J Robertson, Jr

Darin S Lussier

Steven Clarkson

Charles W Brown

Andrew S Foose

Georgios S Zafiris

Colin J Kling

David A Welch

John Harner

Douglas A Welch

Daniel Bernard Kupratis

Gary D Roberge

James W Norris

Sreenivasa R Voleti

Scott A Smith

Raymond P Martina

Jan B Kowza

Wendy P Lopardi

Steven P Shach

Imad Hanhan

Kerry E Muenchow

Eli Cole Warren

David E Valentine

Alan H Epstein

Rajiv A Naik

Corey A Benoit

Edward F Dreger, Iii

Andrew P Berryann

Kevin Andrew Ford

Nathan D Korn

Michael Raymond LaFavor

Erik D Rice

Michael Raymond Lafavor

Scott David Sanicki

Johan Santana

Curt R Hetherington

Chris Freiler

James E Tracy

Raymond C Ward

Dana H Lewis

Jams W Norris

Jr Thomas J Robertson

Johan R Santana

Charles Brown

Chris Freilier

Scott Sanicki

A method for preparing an abradable panel for a rub strip of a fan case of a gas turbine engine includes forming an abradable material into a plurality of panels each comprising an abradable structure; curing the abradable material in the plurality of panels; and installing the plurality of panels into the fan case. The panels can be cured and assembled into a fully assembled rubstrip, and then the assembled rubstrip can be installed into the fan case.

Abradable material and design for jet engine applications

A retention assembly for a fan case liner including a retention bracket including a tab; a damper comprising a forward end opposite an aft end, the damper comprising an exterior surface extending between the forward end and the aft end, the damper having at least one slot formed in the exterior surface; a bracket slot formed in the damper proximate the aft end, the bracket slot configured to receive the tab; and the fan case liner comprising a fan case liner receiver configured to receive the damper, wherein the retention bracket and damper support the fan case liner.

Compliant dampening wedge mount

An abradable material for a rub strip of a gas turbine engine component includes a polymer matrix, and an organic or inorganic filler distributed through the matrix, wherein the abradable material has a compression spring rate profile including: less than 50,000 lb/in at −65° F., less than 35,000 lb/in at room temperature, and less than 35,000 lb/in at 200° F.

In a fan case having an annular outer wall with a plurality of fan case bolt holes there through, bushings are inserted into the fan case bolt hole and are dimensioned to define an annular gap between the bolt hole inner surface and the bushing outer surface. An adhesive material disposed within each annular gap between the bushing and the corresponding fan case bolt hole, with the adhesive material forming a liquid shim separating the bushing outer surface from the bolt hole inner surface.

Method for tight control of bolt holes in fan assembly

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 assembly for a gas turbine engine includes a honeycomb structure. The fan case assembly also includes a septum operatively coupled to the honeycomb structure and located radially inward of the honeycomb structure. The fan case assembly further includes a rubstrip in contact with the septum and located radially inward of the septum.

Fan case assembly for gas turbine engine

A cartridge for a fan case of a gas turbine engine includes an inlet acoustic liner section integrated with a thermally conforming liner section.

Thermally conforming acoustic liner cartridge for a gas turbine engine

A gas turbine engine is provided. The gas turbine engine comprising: a fan section having a fan; and a containment zone encircling the fan, the containment zone comprising: a ballistic liner composed of a plurality of ring segments located radially outward of the fan; wherein each of the plurality of ring segments include two opposing circumferential ends, and wherein the plurality of ring segments are arranged circumferentially around the fan section and the circumferential ends of each of the plurality of ring segments meet at joints to form the ballistic liner.

Ballistic liner install methods

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

A fan section for a gas turbine engine according to an example of the present disclosure includes, among other things, a fan containment case assembly that has an outer case extending about an axis, and a thermally conforming liner assembly radially inward of the outer case. The liner assembly has a shell, a wrap radially outward of the shell, and a ballistic liner between the outer case and the wrap. The wrap has a first fiber construction, and the ballistic liner has a second fiber construction that differs from the first fiber construction in stiffness.

Fan Containment case for gas turbine engines

A capacitance probe monitors the distance between a blade tip and a fan, compressor or turbine case. The capacitance probe may be attached to a liner, and may travel with the liner as it radially expands due to thermal changes. The capacitance probe may include a circuit board sensor with a metallic plate, and one or more capacitors. The metallic plate may be encapsulated within an insulating material. A plurality of soft leads may be in electrical communication with the circuit board sensor, allowing a lower lead weight, reduced size and increased flexibility. The soft leads may also be embedded in the liner. In this way, the capacitance probe can record more accurate distance measurements and promote a gas turbine engine's continued and efficient operation.

Encapsulated soft-lead capacitance probe for a gas turbine engine

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 gas turbine engine includes a liner disposed around a flowpath. The liner has a forward end, a radially outer surface, and a radially inner surface. A hole extends axially into the forward end of the liner between the radially outer surface and the radially inner surface, and an engagement member is partially disposed in the hole and extends axially forward from the forward end of the liner.

Liner attaching scheme

Growing community of inventors

Storrs, CT, United States of America

Mark W Costa