Thermal management system for an aircraft
US11982230B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Aug 14, 2023 |
| Grant date | May 14, 2024 |
| Priority date | — |
| Expiry date | Aug 14, 2043 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2260/213
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A thermal management system for an aircraft comprises a first gas turbine engine, a first thermal bus, a first heat exchanger, and a chiller. The first thermal bus comprises a first heat transfer fluid, with the first heat transfer fluid being in fluid communication, in a closed loop flow sequence, between the first gas turbine engine, the first heat exchanger, and the chiller. Waste heat energy generated by the first gas turbine engine, is transferred to the first heat transfer fluid. The chiller is configured to lower a temperature of the first heat transfer fluid prior to the first heat transfer fluid being circulated through the gas turbine engine. The first heat exchanger is configured to transfer the waste heat energy from the first heat transfer fluid to a dissipation medium.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.