Rolls-Royce Corporation

Rolls-Royce High Temperature Composites Inc.

Ian M Edmonds

Michael J Whittle

Anthony G Razzell

Michael G Abbott

Louise J Gale

Stephan J Pattison

Stephen Harris

Howard James Stone

Emma C Steedman

James C Smith

Edward M Jones

Ayan Bhowmik

Edward Jones

James Smith

Stephen Pattison

Emma Steedman

A method of treating a component adapted for use in a gas turbine engine is described herein. The component may comprise ceramic matrix composite materials. The treatment to the ceramic matrix composite component may reduce or eliminate the wear or damage of crack propagation in the ceramic matrix composite component.

Gas turbine engine with pre-conditioned ceramic matrix composite components

A gas turbine engine system includes an engine component comprising ceramic matrix composite materials, at least one control system configured to control at least a temperature of the engine component, and a controller. The controller includes a degradation map stored therein. The degradation map includes degradation fields, each field defined by a unique range of temperatures and stresses of the component and correlated to different types of degradation of the component. The controller is configured to determine a first temperature and stress of the component and a first field based on the first temperature and stress, determine a second field different from the first and a second temperature and stress that would locate the component in the second field, and instruct the control system to change the temperature of the component from the first to the second temperature to locate the component in the second field.

Gas turbine engine operating schedules for optimizing ceramic matrix composite component life

A component for use in a gas turbine engine is made from ceramic materials. The component is made from a core preform containing ceramic reinforcement fibers. A plurality of preform tows are applied on at least a portion of the core preform and extend along at least a portion of the core preform to provide an outermost surface. The core preform and the plurality of preform tows are infiltrated with ceramic matrix material to form a ceramic matrix composite component.

Ceramic matrix composite vane with hybrid construction

An airfoil for a gas turbine engine is made from ceramic matrix composite materials. The airfoil has an inner surface that defines a cooling cavity in the body and an outer surface that defines a leading edge, a trailing edge, a pressure side, and a suction side of the body. The airfoil is formed with a hollow tube that extends through the body to define a cooling passage that extends from the cooling cavity through the airfoil to provide fluid communication between the cooling cavity and a gas path environment surrounding the airfoil.

Ceramic matrix composite vane with cooling holes and methods of making the same

An airfoil assembly for use in a turbine of a gas turbine engine includes an airfoil that extends radially relative to an axis. The airfoil includes an inner surface that defines a cooling cavity that extends radially into the airfoil and an outer surface that defines a leading edge, a trailing edge, a pressure side, and a section side of the airfoil. The airfoil assembly further includes features for increasing the heat transfer coefficient of the airfoil.

Ceramic matrix composite components with heat transfer augmentation features

A turbine blade of ceramic matrix composite material construction adapted for use in a gas turbine engine includes an airfoil assembly. The airfoil assembly includes an airfoil and at least one reinforcement inset coupled to the airfoil assembly. The reinforcement inset is configured to resist damage to the airfoil assembly due to objects impacting the airfoil assembly.

Ceramic matrix composite aerofoil with impact reinforcements

A hypereutectic chromium alloy consisting of 9 to 12 at % tantalum, 4 to 15 at % silicon, 0 to 7 at % molybdenum, 0 to 7 at % aluminum, 0 to 7 at % titanium, 0 to 5 at % rhenium, 0 to 2 at % silver, 0 to 2 at % hafnium, 0 to 2 at % lanthanum, 0 to 2 at % cerium, 0 to 2 at % yttrium and the balance chromium and incidental impurities. The hypereutectic chromium alloy has good oxidation resistance and good fracture toughness. The chromium alloy may be used to make gas turbine engine turbine blades, turbine vanes, turbine seals, combustion chamber tiles, exhaust nozzle segments or steam turbine components.

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London, United Kingdom

Ian M Edmonds