United Technologies Corporation

Raytheon Technologies Corporation

Rtx Corporation

Darin S Lussier

Thomas J Robertson, Jr

Mark W Costa

Colin J Kling

Sreenivasa R Voleti

Larry Foster

Georgios S Zafiris

James T Roach

John Harner

Christopher M Quinn

Rajiv A Naik

James F O'Brien

Scott A Smith

Raymond P Martina

Imad Hanhan

Kerry E Muenchow

Michael A Weisse

Thomas G Cloft

David R Lyders

Ron I Prihar

Kwan Hui

Jason Elliott

Nicholas D Stilin

George Alan Salisbury

Peter Karkos

Michael Raymond LaFavor

Xuetao Li

Peter Finnigan

Hillary Anne Huttenhower

Royce E Tatton

Michael Raymond Lafavor

Kirk D Stackhouse

Johan Santana

Po-Ching Yeh

Gulperi Aksel

Jr Thomas J Robertson

Jr Thomas Robertson

Hillary A Huttenhower

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 blade includes an airfoil section and a root section that extends in a chord-wise direction between leading and trailing root faces and in a radial direction that is perpendicular to the chord-wise direction from an inner root face to the second end of the airfoil section. The root section defines a dovetail cross-section that is perpendicular to the chord-wise direction. The airfoil section and the root section are comprised of a composite material architecture that includes inter-section fiber plies that each extend from the leading to the trailing edge and from the airfoil section into the root section. Wedges extend in the root section and are interleaved with the inter-section fiber plies. Each of the wedges tapers in the chord-wise direction and the radial direction.

Composite blade with tapered root section

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.

A turbine fan fairing platform is disclosed. The turbine fan fairing platform includes a platform body including a first side portion arranged to abut a first fan blade, a second side portion arranged to abut a second fan blade, and a central portion extending between the first side portion and the second side portion. A seal member is disposed over the platform body. The seal member includes a first side portion over the platform body first side portion, a central portion over the platform body the central portion, and a second side portion over the platform body second side portion. An erosion protection layer is disposed over the seal member over the central portion of the platform body.

Turbine fan fairing platform with protective surface

A method of fabricating a fan case for a gas turbine engine defines a metallic ring including an outer surface and an inner surface. A first composite material is assembled about the outer surface of the metallic ring. A second composite material is assembled about the first composite material. The first composite material and the second material are cured about the metallic ring within a tool to form a first subassembly. The first subassembly is removed from the tool. A fan case assembly for a gas turbine engine and a gas turbine engine are also disclosed.

Co-molded metallic fan case containment ring

A fan case for a gas turbine engine includes an annular liner and an annular case body. The liner has a plurality of liner fiber layers. The case body surrounds the liner. The case body includes a plurality of first and second fiber layers. The first fiber layers extend axially beyond the second fiber layers in axially forward and aft directions and the second fiber layers are interleaved with the first fiber layers. The first fiber layers each have a first fiber architecture and the second fiber layers each have a second, different fiber architecture.

Fan case with interleaved layers

A case for a gas turbine engine includes a plurality of distinct case sections in axial series. The case sections include, in axial order, a flange section, a forward shell section, a containment section, and an aft shell section. The forward shell section, the containment section, and the aft shell section are formed of a plurality of unidirectional roving fiber layers and a plurality of non-crimp fabric layers. The flange section is formed of a second plurality of non-crimp fabric layers. The plurality of unidirectional roving fiber layers do not have stitching or weaves. A ballistic liner is attached with the containment section, and a fiberglass layer encapsulates the plurality of unidirectional roving fiber layers, the plurality of non-crimp fabric layers, and the second plurality of non-crimp fabric layers.

Case with ballistic liner

A reinforced component in accordance with various embodiments includes a metal lug configured to be attached to a secondary component. The reinforced component further includes a composite material integrally formed around the metal lug and configured to be retained in place relative to the secondary component via an attachment between the metal lug and the secondary component.

Composite fan platform lug reinforcement

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

The present disclosure relates generally to a turbine engine case assembly, the turbine engine case assembly including a fan case including an outer frame encircling an axis, the outer frame including an outer frame exterior surface and an outer frame interior surface, at least two mounts disposed on the outer frame exterior surface, wherein the at least two mounts are circumferentially spaced along the outer frame exterior surface, and a compliant attachment device operably coupled to the at least two mounts.

Turbine engine case attachment and a method of using the same

A fan containment case for a gas turbine engine includes a first inner layer and a second layer outside the first inner layer, where the second layer is made of a first material having a first fabric architecture. The fan containment case also includes a third layer outside of the second layer, where the third layer is made of a second material having a second fabric architecture, and at least one of the first material and the first fabric architecture of the second layer is different from the second material and the second architecture, respectively, of the third layer. A fourth outer layer is located outside of the third layer.

Functionally graded composite fan containment case

A preform sheet for a composite component comprises a body section and a flange section. The preform body section includes a plurality of axial tows braided with at least a plurality of first bias tows and a plurality of second bias tows. The preform flange section includes a first braided flange layer and a second braided flange layer. The first braided flange layer is defined by the first and second braided bias tows of the preform body section extending into the flange section. Neither the first nor second braided flange layers have axial tows.

Composite flange from braided preform

The present disclosure relates generally to a system for handling a gas turbine engine fan case. The system includes a composite fan containment case including a case outer surface, a case inner surface, and at least one main case aperture extending from the case outer surface through the case inner surface, and at least one shear puck, the at least one shear puck including a shear puck protrusion; wherein the shear puck protrusion of each of the at least one shear pucks is disposed within a respective one of each of the at least one main case apertures.

Ground handling system for a composite fan case and a method of using the same

A fan housing assembly of a turbofan engine and method of manufacture includes a fan housing that defines a flowpath radially inward, and a groove structure attached to and located aft of the housing for connection to a stationary portion of an outer shell of a thrust reverser. The groove structure includes a base portion concentrically located about an engine axis, and aft and leading legs spaced axially apart from one another and projecting radially outward from the base portion. The fan housing, the base portion, and the aft and leading legs are made of a one-piece composite material.

Growing community of inventors

Berlin, CT, United States of America

Darin S Lussier