Rolls-royce High Temperature Composites Inc.

Rolls-royce North American Technologies Inc.

Kevin Mark Lukhard

Robert J Shinavski

Thomas Tran

Ted Joseph Freeman

Steffan Brown

Sungbo Shim

Pathikumar Sellappan

Thomas E Krause

Timothy Western

In some examples, a multilevel retort assembly. The assembly includes a base defining a base perimeter; and a plurality of shells. Each shell has a diffuser plate support and a perimeter with a substantially similar shape as the base perimeter. The plurality of shells are stacked on each other, mechanically supported by the base, and surround an inner retort volume. The at least one shell of the plurality of shells defines a removable window. The assembly also includes a plurality of diffuser plates, each diffuser plate supported by a corresponding diffuser plate support of the plurality of diffuser plate supports.

Retort with loading window

A method is provided in which a resin coating is applied to a surface of a preform. The resin coating includes a carbonaceous resin and a particulate. The preform is added to a tooling. The preform, which is positioned in the tooling, is cured. The tooling is removed. The resin coating on the surface of the preform is pyrolyzed to form a resin carbon-char layer on the surface of the preform. The preform and the resin carbon-char layer are infiltrated with silicon to form a ceramic matrix composite (CMC) component including a layer of silicon carbide. During the infiltration, the silicon reacts with carbon in the resin carbon-char layer to form the layer of silicon carbide on the preform.

Method for producing a surface layer on a ceramic matrix composite

A turbine vane comprising ceramic matrix composite materials includes a vane support core, an airfoil, and an end wall that at least partially defines a gas path. The turbine vane is formed from a plurality of ceramic plies or preforms that are infiltrated with ceramic matrix material to form a one-piece ceramic matrix composite turbine vane.

Ceramic matrix composite turbine vane and method for making

A turbine vane comprising ceramic matrix composite materials. The turbine vane includes an vane support core, an airfoil, and a pair of end walls that are spaced apart from one another to define a gas path. The turbine vane is formed from a plurality of ceramic plies or preforms that are infiltrated with ceramic matrix material to form a one-piece ceramic matrix composite turbine vane.

A method for infiltrating a porous preform for a gas turbine engine is provided, which comprises providing a chamber for infiltrating a porous preform. The porous preform is positioned within a slurry confinement fixture within the chamber. A vacuum is created in the chamber. A solvent is added to the slurry confinement fixture until a pressure in the chamber is substantially equal to an equilibrium partial pressure of the solvent. A slurry is added to the slurry confinement fixture. The slurry includes the solvent and a particulate. The pressure in the chamber is increased, and the slurry is urged into the porous preform.

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Anaheim, CA, United States of America

Kevin Mark Lukhard