Rolls-royce Corporation

Rolls-royce North American Technologies Inc.

Robert F Proctor

Ted Joseph Freeman

Joseph Peter Henderkott

Quinlan Yee Shuck

Adam Lee Chamberlain

Sean E Landwehr

Aaron D Sippel

Edward Claude Rice

Raymond Ruiwen Xu

Jonathan M Rivers

Jay Edgar Lane

Jonathan Acker

Eric E Wilson

Thomas Nixon

Geoffrey L Gatton

Nathan J Cooper

Jacque Sue Bader

Mark E Bartolomeo

Philip Michael Bastnagel

Maxwell Layman

Brian Drier

Eric Handa

Aaron Martin

Amanda Dawn Graham

Christopher I Hamilton

An assembly for a dual-walled component of a gas turbine engine and methods of forming and repairing a dual-walled component. The assembly includes a cold section part having an outer surface that defines a plurality of impingement apertures, a hot section part including a pre-sintered preform, the hot section part positioned over the outer surface of the cold section part, and a plurality of support structures including the pre-sintered preform, the plurality of support structures positioned between the hot section part and the cold section part, the plurality of support structures separating the hot section part from the cold section part to define at least one cooling channel therebetween.

Dual-walled components for a gas turbine engine

A method of forming a ferrous metal case-hardened layer using additive manufacturing. The method includes delivering, by a material delivery device, a filler material to a surface of a substrate. The substrate includes a first ferrous metal. The filler material includes a second ferrous metal and a carbon-based material. The method also includes directing, by an energy delivery device, an energy toward a volume of the filler material to join at least some of the filler material to the substrate to form a component.

Additive manufactured ferrous components

In some examples, a method for additive manufacturing an article, the method including depositing a filament via a filament delivery device to form at least one track of the deposited filament, the at least one track of the deposited filament forming at least a portion of a preform article, wherein the filament includes a sacrificial binder and a powder, wherein the powder includes a plurality of elongated particles with each respective particle defining a longitudinal axis, wherein the longitudinal axes of the plurality of particles are substantially aligned with each other within the at least one track of the deposited filament; removing substantially all the binder from the at least one track of the preform article to form a powder article; and sintering the powder article to form a sintered article.

Fused filament fabrication with elongated particles

A gas turbine engine includes a turbine shroud assembly with a carrier and a plurality of turbine shroud segments. Each turbine shroud segment includes a blade track segment and a mount assembly. The carrier is arranged to extend circumferentially at least partway around an axis. The blade track segment includes a shroud wall and a mount post that extends radially away from the shroud wall. The mount assembly is configured to couple the blade track segment with the carrier.

Turbine shroud assembly with pinned attachment supplements for ceramic matrix composite component mounting

An article that includes a structured substrate having a macro-porous structure that defines a plurality of pores, and a metallic nano-crystalline coating on at least a portion of the structured substrate, where the metallic nano-crystalline coating defines an average grain size less than about 20 nanometers.

High strength aerospace components

One aspect of the present disclosure includes a turbine vane assembly comprising a vane made from ceramic matrix composite material having an outer wall extending between a leading edge and a trailing edge and between a first end and an opposing second end; an endwall made at least partially from a ceramic matrix composite material configured to engage the first end of the vane; and a retaining region including corresponding bi-cast grooves formed adjacent the first end of the vane and a receiving aperture formed in the endwall; wherein a bond is formed in the retaining region to join the vane and endwall together.

Method of assembly of bi-cast turbine vane

In some examples, a technique includes forming, on a surface of a first layer of material, a second layer of material using an additive manufacturing process. The technique also may include imaging the second layer using a laser imaging device to generate a second layer image. Further, the technique may include determining, by a computing device, whether a thickness of the second layer, in a direction substantially normal to the surface of the first layer of material, is within a defined range of thickness for the second layer.

Additive manufacturing including layer-by-layer imaging

Bi-cast turbine vane

Growing community of inventors

Carmel, IN, United States of America

Robert F Proctor