Heat-transfer fluid for a cooling system of an aircraft turbojet engine
US11230973B2 · kind B2 · utility
0Cited by
2References
13Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Apr 3, 2020 |
| Grant date | Jan 25, 2022 |
| Priority date | — |
| Expiry date | May 30, 2040 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
In a cooling system of an aircraft turbojet engine surrounded by a nacelle, a heat-transfer fluid is circulated that is less flammable than a lubricant (H) for the turbojet engine and liquid at temperatures between −70° C. and +175° C., the heat-transfer fluid (C) being intended to circulate in a closed-circuit circulation duct including a first surface heat-exchanger between the heat-transfer fluid (C) and air (F), at the level of at least one of the outer fairing and the inner fairing of the nacelle, and a second surface heat-exchanger between the heat-transfer fluid (C) and the lubricant (H).
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.