Thermal management system for an aircraft
US12358638B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Aug 14, 2023 |
| Grant date | Jul 15, 2025 |
| Priority date | — |
| Expiry date | Aug 14, 2043 |
Classification
- Technology area (CPC —)General
Abstract
A thermal management system for an aircraft includes a first thermal bus including one or more first heat sources, a heat sink, a vapour compression system, and one or more second heat sources. The vapour compression system includes a compressor, a condenser, a receiver, a first side of a recuperator, an expansion valve, an evaporator, a second side of the recuperator, and the compressor. A first heat flow (Q1) of waste heat energy generated by the first heat sources is transferred via the first heat transfer fluid to the heat sink. A second heat flow (Q2) of waste heat energy generated by the second heat source(s) being transferred via the evaporator to a refrigerant. A third heat flow (Q3) of heat energy in the refrigerant is transferred via the condenser to the first heat transfer fluid. The controller is configured to ensure that: 1.1*Q2<Q3<3.0*Q2.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.