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US 2026/0160205 A1Published application
Thermal management systems for gas turbine engines
AssigneeGeneral Electric Company
InventorsSteven Douglas Johnson, Chirag Kataria, Sanjay Vijayaraghavan, Paul Joseph Kreitzer
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Abstract
A thermal management system for a gas turbine engine includes an oil tank, a pump in fluid communication with the oil tank configured to generate a flow of oil from the oil tank, at least one heat exchanger downstream of the oil tank, and one or more thermal loads downstream of the at least one heat exchanger. The oil tank is formed from a solid-solid phase change material.
Claims18
A thermal management system for a gas turbine engine, comprising:
- an oil source;
- a pump configured to generate a flow of oil from the oil source;
- a first heat exchanger downstream of the oil source;
- a second heat exchanger downstream of the oil source;
- and
- one or more thermal loads downstream of the first heat exchanger and the second heat exchanger;
- wherein the first heat exchanger includes a solid-solid phase change material.
4 more elements
A gas turbine engine, comprising:
- a fan;
- a turbomachine operably coupled to the fan for driving the fan, the turbomachine comprising a compressor section, a combustion section, and a turbine section in serial flow order and together defining a core air flow path;
- and a thermal management system comprising:
- an oil source,
- a pump configured to generate a flow of oil from the oil source,
- a first heat exchanger downstream of the oil source,
- a second heat exchanger downstream of the oil source, and
- one or more thermal loads downstream of the first heat exchanger and the second heat exchanger;
- wherein the first heat exchanger includes a solid-solid phase change material.
6 more elements
Dependencies are inferred from the claim text.