Gas turbine engine heatshield
AssigneeROLLS-ROYCE plc
InventorsLucian INGLEY, David SAVINGS, William T. DITHERIDGE
Life of this patent
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Abstract
A gas turbine engine is provided for an aircraft. The engine includes an engine core comprising a turbine, a compressor, and a core shaft connecting the turbine to the compressor. The engine further includes core casings surrounding the engine core. The engine further includes one or more engine accessories mounted adjacent to the core casings. The engine further includes a self-supporting heatshield positioned between the one or more engine accessories and the core casings. The heatshield is formed of ceramic matrix composite material.
Claims9
A gas turbine engine for an aircraft, the engine including:
- an engine core comprising a turbine, a compressor, and a core shaft connecting the turbine to the compressor;
- core casings surrounding the engine core;
- and
- one or more engine accessories mounted adjacent to the core casings;
- wherein the engine further includes a self-supporting heatshield positioned between the one or more engine accessories and the core casings, the heatshield being formed of ceramic matrix composite material.
Dependencies are inferred from the claim text.