CONTAINMENT RING CAVITY PRESSURIZATION SYSTEM
Number of patents in Portfolio can not be more than 2000
United States of America
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Issued Date -
Feb 6, 2025
app pub date -
Aug 4, 2023
filing date -
Aug 4, 2023
priority date (Note) -
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status (Latency Note)
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Abstract
Aircraft engines and methods of operation thereof are described. The aircraft engines include a fan section, a combustion section, a compressor section comprising an impeller, and a turbine section comprising a vane assembly and a containment cavity defined radially outward from the vane assembly. The fan section, the combustion section, the compressor section, and the turbine section are arranged along an engine axis and an engine shaft operably connects the turbine section to the fan section. Cooling air is supplied from the impeller to an inner diameter of the vane assembly, passed through at least one vane of the vane assembly, and into the containment cavity.
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